Aircraft door system

Abstract

The application relates to the field of aircraft technology and discloses an aircraft cabin door system. The aircraft cabin door system comprises a door frame, a cabin door, a fairing cover, and at least one pair of connecting hinges. The cabin door comprises a cabin door body and the fairing cover covers the outer side surface of the cabin door body. The cabin door is rotationally connected to the door frame through the connecting hinges. The rotation axis of the connecting hinges is arranged in the side wall of the door frame, so that the surface of the fairing cover is flush with the outer surface of the side wall of the door frame when the cabin door is closed. The cabin door hinge structure of the application adopts an embedded design, can ensure high bearing capacity, realize smooth and flat outer skin surface, and has the functions of preventing silt and wear resistance.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, and more particularly to an aircraft door system. Background Technology

[0002] Existing cabin door designs mostly employ external or semi-external hinge structures, with the hinge pins positioned close to the fuselage skin surface. Because the hinge pins need sufficient diameter to withstand bending moments and shear forces, they often protrude from the skin, forming noticeable bulges. This not only affects the aesthetics but also increases aerodynamic drag and makes them prone to accumulating dirt. Furthermore, the exposed hinge pins and bearings are susceptible to abrasion from mud, sand, pebbles, and other contaminants splashed from the ground during landing, causing surface scratches and wear, affecting service life and reliability. Simultaneously, traditional hinge layouts often interfere with the cabin door sealing structure, impacting the cabin's waterproofing performance. Utility Model Content

[0003] The purpose of this application is to provide an aircraft door system. The door hinge structure of this application adopts a built-in design, which can ensure high load-bearing capacity while achieving a smooth and flat outer skin surface and has anti-mud and sand wear-resistant functions.

[0004] To address the aforementioned technical problems, this application provides an aircraft door system, comprising: a door frame; a door, the door including a door body and a fairing cover, the fairing cover covering the outer surface of the door body; and at least one pair of connecting hinges, the door being rotatably connected to the door frame via the connecting hinges; the rotation axis of the connecting hinges is located within the side wall of the door frame, so that when the door is closed, the surface of the fairing cover is flush with the outer surface of the side wall of the door frame.

[0005] Optionally, the connecting hinge includes a rotating shaft, a hatch hinge, and a door frame hinge. The rotating shaft is located inside the side wall of the door frame, the hatch hinge is connected to the hatch body, and the door frame hinge is connected to the door frame.

[0006] Optionally, the hatch hinge includes a pair of hatch hinge arms, and the door frame hinge includes a pair of door frame hinge arms, wherein each of the hatch hinge arms, each of the door frame hinge arms, and each of the rotating shaft portions are connected in pairs.

[0007] Optionally, each of the hatch hinge arms and the door frame hinge arms is provided with a hatch hinge through hole and a door frame hinge through hole for the through connection of the rotating shaft.

[0008] Optionally, the rotating shaft includes a rotating shaft bushing and a hinge bolt, the rotating shaft bushing being inserted into the hinge through hole of the hatch.

[0009] Optionally, the axial length of the pivot bushing is greater than the axial length of the hatch hinge through hole.

[0010] Optionally, the end of the pivot bushing is provided with a cap, and after the hinge bolt is inserted into the pivot bushing, it is screwed into the hinge through hole of the door frame until the end abuts against the cap.

[0011] Optionally, the door frame hinge arm is provided with at least one limiting block so that the door hinge arm can rotate relative to the door frame hinge arm about the rotation axis within a target angle range.

[0012] Optionally, the door frame edge is provided with at least one pair of grooves, which are open to the outside and top of the aircraft; each of the rotating shaft portions is adapted to be disposed in the corresponding groove, and the fairing includes a cover body portion and at least one pair of cover extension portions, which are used to cover the outer surface of the groove when the door is closed, so that the outer surface of the cover extension portion is flush with the outer surface of the door frame.

[0013] Optionally, the rotating shaft bushing is coated with grease and then inserted into the hatch hinge through hole.

[0014] The door hinge structure of this application adopts a built-in design, which can ensure high load-bearing capacity while achieving a smooth and flat outer skin surface, and has anti-mud and sand wear-resistant functions. Attached Figure Description

[0015] Figure 1 The diagram shown is a partial structural schematic of the aircraft door system according to an embodiment of this application. Figure 2 Displayed as Figure 1 A magnified view of a portion of position A in the middle; Figure 3 The diagram shown is a structural schematic of the connecting hinge in an embodiment of this application. Figure 4 Displayed as Figure 3 Decomposition diagram of position B in the middle; Figure 5 The diagram shown is a structural schematic of a hinge bolt component according to an embodiment of this application. Figure 6 The diagram shown is a structural schematic of the groove implemented in this application; Figure 7 The diagram shown is an external view of the hatch after it has been closed, according to an embodiment of this application. Detailed Implementation

[0016] 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.

[0017] 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.

[0018] 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.

[0019] 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.

[0020] The term "vertical takeoff and landing (VTOL) aircraft" is defined as an air transport system of any size that has at least one propeller as its propulsion source. The term "VTOL aircraft" can include both "manned" and "unmanned" air transport systems. A manned VTOL aircraft can mean an air transport system carrying one or more human passengers, none of whom have control over the VTOL aircraft. A manned VTOL 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 VTOL aircraft. An unmanned VTOL 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.

[0021] 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).

[0022] Embodiments of this application are described below with reference to the accompanying drawings, such as Figure 1 As shown in the figure, this application provides an aircraft door system, including: a door frame 1, a door 2, and a pair of connecting hinges 3. The door 2 includes a door body 21 and a fairing 22, with the fairing 22 covering the outer surface of the door body 21. The door 2 is rotatably connected to the door frame 1 via the connecting hinges 3. The rotation axis X of the connecting hinges 3 is located inside the side wall of the door frame 1, so that when the door 2 is closed, the surface of the fairing 22 is flush with the outer surface of the side wall of the door frame 1 and presents a naturally extending surface.

[0023] Specifically, such as Figure 2 As shown, the sidewall of the door frame 1 has a certain thickness, with its outer side flush with the outer surface of the aircraft and its inner side being the inner surface of the aircraft. A raised band 11 extends from the inner side of the door frame towards the center of the door opening, and a sealing ring or sealing strip can be installed on the raised band 11, serving as the main sealing band of the hatch. When the hatch 2 is closed, the hatch body 21 and the raised band 11 cooperate to press the sealing ring, achieving an airtight seal between the hatch and the door frame, ensuring stable cabin pressure in the high-altitude environment. A connecting hinge 3 is embedded inside this sidewall, positioned below and to the outside of the raised band 11 to avoid interfering with the sealing structure when the hatch is closed.

[0024] It should be noted that, in the embodiments of this application, "outer side" refers to the outer side of the aircraft, and "inner side" refers to the inner side of the aircraft.

[0025] In this embodiment, the fairing cover 22 is made of lightweight composite material, and its outer surface is aerodynamically optimized to effectively reduce airflow disturbance and drag during flight.

[0026] The edge of the rectifier cover 22 adopts a smooth transition design, with no obvious step difference at the junction with the outer surface of the door frame 1, which further improves the continuity of the aerodynamic shape.

[0027] In one embodiment, the fairing 22 is doubly secured to the door body 21 by a high-strength adhesive and mechanical fasteners, ensuring structural integrity even under high-speed flight or severe vibration conditions. The specific connection method can be selected based on material properties and assembly processes.

[0028] In this embodiment, the number of connecting hinges 3 is one pair. However, it is understood that the number of connecting hinges 3 can also be other, such as two or more. The specific number can be adjusted according to the size, weight, and force distribution requirements of the hatch to ensure the stability of the hatch opening and closing and the structural reliability. In different application scenarios, the number of connecting hinges can be flexibly designed to adapt to the sealed hatch structure of small UAV cabins or large manned aircraft, thereby improving the versatility and scalability of the system.

[0029] In this embodiment, the connecting hinge 3 is located at the bottom of the door frame 1. However, it is understood that the connecting hinge 3 can also be located at other positions on the door frame 1, such as the top or side, to accommodate the needs of different door opening methods, such as upward-opening, downward-opening, or side-opening structures. The flexible arrangement of the hinge position can effectively optimize the door opening angle and space occupation, and is especially suitable for compact aircraft layouts.

[0030] like Figure 3 As shown, the connecting hinge 3 includes a rotating shaft portion 30, a door hinge 31, and a door frame hinge 32. The rotating shaft portion 30 is located inside the side wall of the door frame 1 to prevent it from protruding from the outer surface of the aircraft. The door hinge 31 includes a pair of door hinge arms 310 and a door fixing portion 311. The door fixing portion 311 of the door hinge 31 is connected to the door body 21 and is connected to the side of the door body 21. The specific connection method can be flexibly adjusted according to the actual structural layout. For example, riveting, bolting, or integral molding processes can be used to ensure the stability of torque transmission and connection strength.

[0031] The door frame hinge 32 includes a pair of door frame hinge arms 320 and a door frame fixing part 321, with the door frame fixing part 321 connected to the door frame 1. Of course, in some embodiments, the door frame hinge 32 is not limited to being connected to the door frame 1; the door frame hinge 32 can extend and connect to the interior of the aircraft, such as to the aircraft floor, thereby enhancing the overall structural stability and load-bearing capacity. The specific connection method can be flexibly adjusted according to the actual structural layout; for example, riveting, bolting, or integral molding processes can be used to ensure that the hinge system has sufficient strength and reliability when bearing the weight of the door and flight loads.

[0032] A pair of hatch door hinge arms 310, a pair of door frame hinge arms 320, and a pair of rotating shafts 30 are connected in pairs to form a stable hinge structure, enabling the hatch to rotate smoothly around the rotating shafts 30 to achieve opening and closing actions. The hatch door hinge arms and the door frame hinge arms are connected by high-precision pins to ensure that there is no jamming or loosening during the movement.

[0033] like Figure 4As shown, the end of the door frame hinge arm 320 is provided with a door frame hinge through hole 3200 for the rotating shaft 30 to pass through, and the end of the hatch hinge arm 310 is provided with a hatch hinge through hole 3100 for the rotating shaft 30 to pass through. The hatch hinge through hole 3100 and the door frame hinge through hole 3200 are coaxially arranged to ensure the smooth rotation of the rotating shaft 30.

[0034] like Figure 4 and Figure 5 As shown, the rotating shaft portion 30 includes a rotating shaft bushing 300 and a hinge bolt 301. The rotating shaft bushing 300 is embedded in the door hinge through hole 3100, and the hinge bolt 301 passes through the rotating shaft bushing 300 and is fixed in the door frame hinge through hole 3200, forming a stable rotation fulcrum. The rotating shaft bushing can be made of a self-lubricating wear-resistant material, which can effectively reduce frictional wear during long-term use and improve the service life of the hinge system. The hinge bolt 301 and the door frame hinge through hole 3200 can be connected by a suitable thread to achieve a secure assembly, while facilitating disassembly and maintenance.

[0035] Furthermore, such as Figure 4 As shown, the end of the pivot bushing 300 is provided with a cap 300a. When assembling the hinge, the pivot bushing 300 is pre-inserted into the door hinge through hole 3100, the through hole of the pivot bushing 300 is axially aligned with the door frame hinge through hole 3200, the hinge bolt 301 is inserted into the pivot bushing 300 and then screwed into the door frame hinge through hole 3200, and finally the end of the hinge bolt 301 abuts against the cap 300a, thereby firmly limiting the pivot bushing and preventing it from moving axially during use.

[0036] The cap 300a effectively prevents the hinge bolt 301 from entering the door frame hinge through hole 3200 too deeply, thus avoiding the hinge bolt 301 completely jamming the hatch hinge arm 310. Simultaneously, the axial length of the pivot bushing 300 is slightly greater than the axial length of the hatch hinge through hole 3100, ensuring that both ends of the pivot bushing 300 are appropriately exposed. This creates a certain gap between the hatch hinge arm 310 and the door frame hinge arm 320, preventing friction between the hatch hinge arm 310 and the door frame hinge arm 320 due to thermal expansion and contraction or assembly errors, thereby ensuring smooth hatch opening and closing. This gap design also considers the need for slight deformation of the material under extreme temperature environments, ensuring the hinge system maintains stable performance under alternating high and low temperature conditions. The exposed portion of the pivot bushing is rounded to reduce the risk of stress concentration.

[0037] In one embodiment, such as Figure 4As shown, at least one limiting block 4 is provided on the door frame hinge arm 320 to allow the hatch hinge arm 310 to rotate relative to the door frame hinge arm 320 around the rotation axis 30 within a target angle range. The limiting block 4 abuts against the end of the rotation trajectory of the hatch hinge arm 310, limiting its maximum opening angle and preventing excessive opening of the hatch from causing structural damage or safety hazards.

[0038] The limiting block 4 can be integrally formed with the door frame hinge arm 320, or it can be fixed to the door frame hinge arm 320 with bolts. Its position is adjustable, facilitating precise alignment during assembly. Simultaneously, the limiting block uses an elastic, wear-resistant material to cover the metal substrate, absorbing impact energy and reducing collision noise, thus improving user comfort. The limiting block's position is precisely designed according to the actual opening requirements of the hatch, ensuring safe and reliable operation.

[0039] Optionally, the edge of the door frame 1 is provided with at least a pair of grooves 10, which are open to the outside and top of the aircraft. The rotating shaft 30 is adapted to be disposed in the corresponding groove 10, so that the door slides along the groove during opening, realizing the guiding and positioning functions. At the same time, the rotating shaft 30 is disposed in the groove, and its shaft rotates stably within the groove, avoiding direct exposure to the external environment. This effectively prevents dust, snow or foreign objects from entering and causing rotational jamming, ensuring the reliable operation of the hinge system in complex environments.

[0040] like Figure 7 As shown, the fairing 22 includes a main body portion 220 and at least one pair of fairing extension portions 221. When the hatch rotates about its pivot axis, the protruding fairing extension portions 221 rotate into the recess 10. When the hatch 2 is closed, it covers the hinge mounting space and is flush with the outer surface of the aircraft in the closed state, presenting a naturally extended surface. This ensures a clean aerodynamic plane, reduces drag, and improves the aerodynamic efficiency and overall appearance of the aircraft. The fit between the fairing extension portions 221 and the recess 10 has a preset interference fit, ensuring that the fairing remains stable and fitted even under vibration, preventing loosening or flutter. Furthermore, the pivot bushing 300 and the hatch hinge arm 31 are coated with grease. The grease is a synthetic-based lubricant that is resistant to high and low temperatures and oxidation, and can maintain stable lubrication performance within a temperature range of -50℃ to 150℃, effectively reducing the coefficient of friction between the pivot and the bushing and extending the service life of the hinge system. At the same time, the grease has good adhesion and anti-leakage properties, and can continue to function under long-term vibration and frequent opening and closing conditions, ensuring smooth and easy hatch operation.

[0041] Furthermore, a sealing strip is arranged above the groove 10. To ensure that the introduction of the hinge structure does not affect the airtightness of the cabin, the sealing strip is made of weather-resistant rubber material and fits tightly against the mating surface of the rotating shaft and the groove. It can maintain elastic sealing performance even under drastic temperature changes and high humidity environments, effectively blocking external airflow infiltration and moisture intrusion, and ensuring the stability of the cabin environment.

[0042] Compared with the prior art, the present invention has the following significant advantages: Aesthetically pleasing and with excellent aerodynamic performance: By embedding the rotating shaft inside the skin and adopting a groove + hatch skin protrusion cover design, the surface of the outer skin is made as smooth and continuous as possible, eliminating the "bulge" phenomenon in traditional solutions and improving the overall appearance quality and aerodynamic performance. Strong protective performance: The hinge shaft and bearing structure are completely embedded inside the body, effectively preventing them from being scratched or impacted by foreign objects such as mud and gravel during take-off and landing, thus extending their service life. Easy maintenance: The hinge assembly can be inspected and replaced through the inside of the hatch when it is open; Good sealing compatibility: The hinge layout avoids the sealing area, and together with the sealing measures, it ensures that the hatch still has good waterproof performance when closed.

[0043] 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. An aircraft door system, characterized in that, include: Door frame (1); hatch (2), the hatch (2) includes a hatch body (21) and a fairing cover (22), the fairing cover (22) covering the outer surface of the hatch body (21); and at least one pair of connecting hinges (3), the hatch (2) being rotatably connected to the door frame (1) via the connecting hinges (3); the rotation axis of the connecting hinges (3) is located inside the side wall of the door frame (1) so that when the hatch (2) is closed, the surface of the fairing cover (22) is flush with the outer surface of the side wall of the door frame (1).

2. The aircraft door system according to claim 1, characterized in that, The connecting hinge (3) includes a rotating shaft (30), a hatch hinge (31) and a door frame hinge (32). The rotating shaft (30) is located inside the side wall of the door frame (1). The hatch hinge (31) is connected to the hatch body (21). The door frame hinge (32) is connected to the door frame (1).

3. The aircraft door system according to claim 2, characterized in that, The hatch hinge (31) includes a pair of hatch hinge arms (310), and the door frame hinge (32) includes a pair of door frame hinge arms (320), wherein each of the hatch hinge arms (310), each of the door frame hinge arms (320) and each of the rotating shaft portions (30) are connected in pairs.

4. The aircraft door system according to claim 3, characterized in that, Each of the aforementioned door hinge arm (310) and door frame hinge arm (320) is provided with a door hinge through hole (3100) and a door frame hinge through hole (3200) for the through connection of the rotating shaft part (30).

5. The aircraft door system according to claim 4, characterized in that, The rotating shaft (30) includes a rotating shaft bushing (300) and a hinge bolt (301), the rotating shaft bushing (300) being inserted into the door hinge through hole (3100).

6. The aircraft door system according to claim 5, characterized in that, The axial length of the pivot bushing (300) is greater than the axial length of the hatch hinge through hole (3100).

7. The aircraft door system according to claim 5, characterized in that, The end of the pivot bushing (300) is provided with a cap (300a). After the hinge bolt (301) is inserted into the pivot bushing (300), it is screwed into the hinge through hole (3200) of the door frame until the end abuts the cap (300a).

8. The aircraft door system according to claim 3, characterized in that, At least one limiting block (4) is provided on the door frame hinge arm (320) so that the door hinge arm (310) rotates relative to the door frame hinge arm (320) within a target angle range around the rotation axis (30).

9. The aircraft door system according to claim 2, characterized in that, The door frame (1) has at least one pair of grooves (10) on its edge, the grooves (10) being open to the outside and above of the aircraft; each of the rotating shaft portions (30) is adapted to be disposed in the corresponding groove (10); the fairing cover (22) includes a cover body portion (220) and at least one pair of cover extension portions (221), the cover extension portions (221) being used to cover the outer surface of the groove (10) when the door (2) is closed, so that the outer surface of the cover extension portion (221) is flush with the outer surface of the door frame (1).

10. The aircraft door system according to claim 5, characterized in that, The rotating shaft bushing (300) is coated with grease and then inserted into the hatch hinge through hole (3100).

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