Aircraft and door stair system therefor

Abstract

The application relates to the field of aircraft technology and discloses an aircraft and a door ladder system thereof. The aircraft door ladder system comprises a cabin door body and a ladder mechanism arranged on the inner side of the cabin door body. The cabin door body is rotationally connected with the aircraft and is used for opening or closing the entrance of the aircraft to form an unfolded state and a folded state. The ladder mechanism comprises a plurality of steps. When in the unfolded state, the steps are unfolded from the entrance to the ground so that a user can enter the interior of the aircraft along the steps. When in the folded state, the steps are automatically folded to the cabin door body. The door ladder system of the application can be automatically folded and does not occupy the interior space of the cabin, thereby improving the convenience of passengers getting on and off the aircraft.

Description

Technical Field

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

[0002] Small aircraft commonly use door ladder systems to improve the convenience of passengers getting on and off the plane, but this design significantly occupies cabin space, resulting in a reduction in the effective volume of the passenger cabin or cargo hold, which directly affects passenger capacity or cargo loading capacity. Utility Model Content

[0003] The purpose of this application is to provide an aircraft and its door ladder system. This application adopts an automatically foldable door ladder system that does not occupy cabin space and improves the convenience of passengers getting on and off the aircraft.

[0004] To address the aforementioned technical problems, this application provides an aircraft door and ladder system, comprising: a door body and a step mechanism disposed inside the door body; the door body is rotatably connected to the aircraft and is used to open or close the aircraft's entrance / exit to form an deployed state and a retracted state; the step mechanism includes multiple steps, which are configured such that in the deployed state, the multiple steps extend from the entrance / exit to the ground, allowing a user to enter the aircraft's interior along the steps; and in the retracted state, the steps automatically retract towards the door body.

[0005] This application provides an aircraft, including a door frame, an upper cabin door, and an aircraft door and ladder system as described above, wherein the upper cabin door and the aircraft door and ladder system are rotatably disposed within the door frame to open or close the entrance and exit of the aircraft.

[0006] Optionally, the pedal is rotatably connected to the inside of the hatch body via a hinge. When the hatch body is in the retracted state, the pedal rotates vertically downward under the action of gravity, so that the pedal automatically moves towards the hatch body.

[0007] Optionally, during the rotation of the hatch body from the retracted state to the unfolded state, the pedal is subjected to centrifugal force and rotates away from the hatch body, eventually coming to rest in a horizontal state.

[0008] Optionally, when the pedal is in a horizontal position, at least one side abuts against the inside of the hatch body.

[0009] Optionally, the various pedals are connected together by ropes.

[0010] Optionally, it also includes a handrail mechanism, which unfolds to one side of the door body when the door body is in the unfolded state to facilitate user gripping, and folds into the aircraft interior and retracts towards the door body when the door body is in the retracted state.

[0011] Optionally, the handrail mechanism includes a first link and a second link that are rotatably connected to each other, the first link being connected to the hatch body and the second link being connected to the aircraft.

[0012] Optionally, the first link includes a first straight rod and a second straight rod connected to each other, the first straight rod and the second straight rod intersecting at an obtuse angle.

[0013] Optionally, the number of pedals is three.

[0014] This application uses an automatically foldable boarding ladder system that does not occupy cabin space, thus improving the convenience of passengers boarding and alighting. Attached Figure Description

[0015] Figure 1 The diagram shown is a structural schematic of the aircraft cabin door in the unfolded state according to an embodiment of this application.

[0016] Figure 2 The diagram shown is a structural schematic of the door and ladder system in the deployed state according to an embodiment of this application.

[0017] Figure 3 Displayed as Figure 2 A magnified view of a portion of position A in the middle;

[0018] Figure 4 The diagram shown is a structural schematic of the door ladder system in the retracted state according to an embodiment of this application.

[0019] Figure 5 The diagram shown is a structural schematic of a doorway system with a handrail mechanism according to an embodiment of this application.

[0020] Figure 6 Displayed as Figure 5 A magnified view of a portion of position B in the middle;

[0021] Figure 7 Displayed as Figure 2 A magnified view of the area at position C in the middle;

[0022] Figure 8 The diagram shows a cross-sectional view of the ball-matching mechanism along its central axis, as described in an embodiment of this application.

[0023] Figure 9 Displayed as Figure 1 A magnified view of the area at position D in the middle;

[0024] Figure 10The image shown is an exterior view of the aircraft with the cabin door retracted, as described in this application embodiment.

[0025] Figure 11 Displayed as Figure 10 A sectional view of line A-A';

[0026] Figure 12 Displayed as Figure 11 A magnified view of the area at position E in the middle;

[0027] Figure 13 The diagram shown is a structural schematic of the upper hatch in the unfolded state according to an embodiment of this application.

[0028] Figure 14 This is a schematic diagram of the first state of the door and ladder system during the deployment process according to an embodiment of this application.

[0029] Figure 15 This is a schematic diagram showing the second state of the door and ladder system during deployment, as described in an embodiment of this application.

[0030] Figure 16 The diagram shown is a structural schematic of the third state of the door and ladder system during the deployment process according to an embodiment of this application. Detailed Implementation

[0031] 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.

[0032] 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.

[0033] 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.

[0034] 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.

[0035] 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).

[0036] Embodiments of this application are described below with reference to the accompanying drawings, such as Figure 1 As shown in the figure, this application embodiment provides an aircraft door and ladder system applied to an aircraft 100. The door and ladder system specifically includes: a door body 1 and a step mechanism 2. The step mechanism 2 is disposed on the inner side of the door body 1, which is consistent with the inner side of the aircraft 100. The door body 1 is rotatably connected to the aircraft 100 and is used to open or close the entrance 10 of the aircraft 100, thereby forming the deployed state and the retracted state of the door and ladder system, respectively.

[0037] The stair mechanism 2 includes multiple steps 20, which are configured to extend from the entrance 10 to the ground when in the deployed state, so that users can enter the interior of the aircraft 100 along the steps 20, and the steps 20 automatically retract toward the door body 1 when in the retracted state.

[0038] Specifically, such as Figure 2 As shown, the pedal 20 is rotatably connected to the inside of the door body 1 via pedal hinges 21, and each pedal 20 is connected to a pair of pedal hinges 21. The door body 1 is rotatably connected to the aircraft 100 via a pair of door hinges 22, one end of which is connected to the aircraft 100, and the other end is connected to the door body 1. With the rotation of the door hinges 22, the door ladder system can open or close the entrance 10 of the aircraft 100 to form the deployed state and the retracted state of the door ladder system, respectively.

[0039] It should be noted that the rotation of the hatch hinge 22 can be manual, electric or hydraulic, and those skilled in the art can set it reasonably according to the actual situation.

[0040] During the rotation of the hatch body 1 from the retracted state to the deployed state, the step 20 rotates away from the hatch body 1 under the action of centrifugal force. When the door ladder system is in the deployed state, the step 20 remains in a horizontal state to facilitate the user's entry into the aircraft 100 via the step 20. However, it is understood that the step 20 can also be rotated through a corresponding mechanical mechanism.

[0041] In one embodiment, the pedal 20 is mechanically limited to a horizontal position by the pedal hinge 21.

[0042] In one embodiment, such as Figure 3 As shown, when the pedal 20 is in the horizontal position, at least one side 201 of the pedal 20 abuts against the inner surface of the hatch body 1, thereby limiting the pedal 20 and keeping it in a horizontal state.

[0043] Furthermore, in some embodiments, such as Figure 3 As shown, each pedal 20 is provided with a fixing part 23 for fixing the rope 24. The pedals 20 are connected together by the rope 24, which further stabilizes each pedal 20, prevents shaking, reduces the stress on the pedal hinge 21, and enhances safety.

[0044] In this embodiment, there are 3 pedals 20, but it is understood that there is no particular limitation on the specific number of pedals 20, and those skilled in the art can set them reasonably according to the actual situation.

[0045] like Figure 4 As shown, when the door ladder system is in the retracted state, that is, when the cabin door body 1 is in the retracted state, the step 20 rotates vertically downward under the action of gravity, and the step 20 automatically moves towards the cabin door body 1 and retracts. This automatic folding and retracting door ladder system does not require an additional drive mechanism and does not occupy the cabin interior space, thus improving the utilization rate of cabin space.

[0046] In one embodiment, such as Figure 5 and Figure 6 As shown, the door and stair system also includes a handrail mechanism 3. When the door body 1 is in the unfolded state, the handrail mechanism 3 unfolds to one side of the door body 1 to facilitate the user to hold the handrail mechanism 3 when entering the aircraft. When the door body 1 is in the retracted state, the handrail mechanism 3 folds into the aircraft 100 and retracts towards the door body 1.

[0047] Specifically, such as Figure 1As shown, the handrail mechanism 3 includes a first link 31 and a second link 32 that are rotatably connected to each other. The first link 31 is connected to the hatch body 1, and the second link 32 is connected to the aircraft 100. Figure 5 and Figure 6 As shown, the first link 31 includes a first straight rod 311 and a second straight rod 312 that are connected to each other, and the first straight rod 311 and the second straight rod 312 intersect at an obtuse angle.

[0048] like Figure 6 As shown, a groove space 11 is provided at the connection between the hatch body 1 and the first connecting rod 31. A connecting part 12 that is rotatably connected to the first connecting rod 31 is provided in the groove space 11, wherein the first straight rod 311 moves within the groove space 11.

[0049] like Figure 4 As shown, when the door and ladder system is in the retracted state, the first link 31 and the second link 32 fold together at the edge of the hatch, saving interior space. Figure 1 As shown, when the door ladder system is in the deployed state, the first link 31 and the second link 32 are deployed accordingly, making it convenient for users to grasp when walking along the step 32 and ensuring boarding safety.

[0050] In addition, in some embodiments, the door ladder system may also be connected to ropes that connect to the aircraft body. There are no particular restrictions on the specific structure, and those skilled in the art can make reasonable settings according to the actual situation.

[0051] The aircraft in this application uses an automatically foldable boarding ladder system that does not occupy cabin space, thus improving the convenience of passengers getting on and off the aircraft.

[0052] In one embodiment, such as Figure 7 and Figure 8 As shown, the hatch body 1 is provided with a pair of ball-operated mechanisms 33. The ball-operated mechanism 33 includes a ball 331 and a biasing member 332 disposed inside the outer shell 330. Under the action of the compressive force, the ball 331 can enter the outer shell 330, and under the action of the biasing member 332, the ball 33 extends out of the outer shell 330 when the compressive force is released. The number of ball-operated mechanisms 33 is not specifically limited.

[0053] like Figure 9 As shown, the aircraft 100 is provided with a pair of ball-bearing grooves 34 that match the ball-bearing mechanism 33. When the door ladder system is retracted, the ball-bearing 331 is squeezed from outside the ball-bearing groove 34 into the ball-bearing groove 34, thereby locking the door ladder system in the door frame of the aircraft 100.

[0054] When the door ladder system is moved from the retracted state to the extended state, the spring force of the corresponding biasing member 332 must be overcome to push the catch ball 331 out of the corresponding catch ball groove 34, thereby opening the door ladder system. The catch ball mechanism 33 and the catch ball groove 34 are designed so that the door ladder system can keep the hatch closed without a large external force. When it is necessary to close or open the door ladder system, only a light push or touch is needed to open or close the door ladder system.

[0055] In this embodiment, the biasing element 332 is a spring, but it is understood that there are no particular restrictions on the specific structure, and those skilled in the art can set it reasonably according to the actual situation.

[0056] like Figures 10 to 16 As shown, this application embodiment also provides an aircraft 100, including a door frame 4, an upper cabin door 5, and a door ladder system 6 of any of the above. The upper cabin door 5 and the door ladder system 6 are rotatably disposed within the door frame 4. The upper cabin door 5 and the door ladder system 6 rotate around the door frame 4 respectively to open or close the entrance 10 of the aircraft 100.

[0057] Specifically, the upper hatch 5 is rotatably connected to the door frame 4 via hinges. For example... Figure 4 As shown, one or more telescopic struts 7 are connected between the upper hatch 5 and the door frame 4. A first fixing part 71 is installed on the inner side of the upper hatch 5 near the top, and a second fixing part 72 is installed on the door frame 4 on the side of the upper hatch 5 at the lower position. The two ends of the telescopic strut 7 are connected to the first fixing part 71 and the second fixing part 72 respectively, so that when the upper hatch 5 is closed, the telescopic strut 7 is compressed and can abut against the first fixing part 71 of the upper hatch 5 in the vertical direction, thereby pressing the upper hatch 5 tightly.

[0058] When the upper hatch 5 is pushed outward by force, and the angle between the upper hatch 5 and the telescopic support rod 7 is greater than a preset angle, the compressed telescopic support rod 7 automatically opens the upper hatch 5 outward during the pressure release process, thereby saving the user's effort. In one embodiment, the preset angle is 15-22 degrees, preferably 20 degrees. However, it is understood that those skilled in the art can adjust the positions of the first fixing part 71 and the second fixing part 72 according to the actual situation for reasonable settings.

[0059] It should be noted that the telescopic strut 7 can be pneumatic or hydraulically driven, and those skilled in the art can set it appropriately according to the actual situation.

[0060] In one embodiment, the upper cabin door 5 is also equipped with a large area of ​​glass to increase the passenger's field of vision.

[0061] In the embodiments of this application, such as Figure 12As shown, the upper hatch 5 is also equipped with a door lock 8. The door lock 8 includes an outer handle on the outside, an inner handle on the inside, and a door lock structure inside the hatch. The specific structure is not limited, and those skilled in the art can set it reasonably according to the actual situation.

[0062] like Figure 11 and Figure 12 As shown, the bottom of the upper hatch 5 is provided with a lower protrusion 50, and the top of the door ladder system 6 is provided with an upper protrusion 60. When the upper hatch 5 and the door ladder system 6 are in the retracted state, the lower protrusion 50 and the upper protrusion 60 are configured to at least partially overlap in the horizontal direction and be offset from each other in the vertical direction.

[0063] In this embodiment, the lower protrusion 50 is located on the bottom outer side of the upper cabin door 5, and the upper protrusion 60 is located on the top inner side of the door ladder system 6. When the upper cabin door 5 and door ladder system 6 are in the retracted state, the upper cabin door 5 abuts against the door ladder system 6 inward. A door lock 8 is provided on the upper cabin door 5, which locks the upper cabin door 5 while simultaneously abutting and fixing the door ladder system 6. When it is necessary to open the aircraft cabin door, the upper cabin door 5 must be unlocked first via the door lock 8 before the door ladder system 6 can be opened. This design on the double-opening doors allows the cabin door to be opened or locked with only one unlocking or locking operation.

[0064] However, it is understood that in another embodiment, the lower protrusion 50 can be provided on the bottom inner side of the upper hatch 5, the upper protrusion 60 can be provided on the top outer side of the door ladder system 6, and the door lock 8 can be provided on the door ladder system 6. The door lock 8 locks the door ladder system 6 and also supports and fixes the upper hatch 5, so that unlocking or locking can be achieved in one go.

[0065] In the embodiments of this application, the lower protrusion 50 and the upper protrusion 60 are basically the same in height in the horizontal direction. However, it is understood that the specific structure and height of the lower protrusion 50 and the upper protrusion 60 are not limited, and those skilled in the art can set them reasonably according to the actual situation.

[0066] This design, with doors opening in opposite directions, allows for the opening or locking of both doors with just one door. The combined effect of both doors maximizes the door opening area, providing passengers with ample space to move in and out.

[0067] Figure 10 The upper cabin door 5 and the door ladder system 6 are shown in their closed state, retracted within the door frame 4. Figure 13 The upper hatch 5 is shown to be open. Figures 14 to 16 The process of the door ladder system 6 rotating from the retracted state to the extended state is shown.

[0068] 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 and ladder system, characterized in that, include: The cabin door body (1) and a step mechanism (2) disposed inside the cabin door body (1); the cabin door body (1) is rotatably connected to the aircraft (100) for opening or closing the entrance (10) of the aircraft (100) to form an unfolded state and a retracted state; the step mechanism (2) includes a plurality of steps (20), the step mechanism (2) being configured such that when the cabin door body (100) is unfolded from the entrance (10) to the ground, so that the user can enter the interior of the aircraft (100) along the steps (20); when the cabin door body (100) is retracted, the steps (20) automatically move toward the cabin door body (1).

2. The aircraft door and ladder system according to claim 1, characterized in that, The pedal (20) is rotatably connected to the inside of the hatch body (1) via a hinge (21). When the hatch body (1) is in the retracted state, the pedal (20) rotates vertically downward under the action of gravity, so that the pedal (20) automatically moves towards the hatch body (1).

3. The aircraft door and ladder system according to claim 1, characterized in that, During the rotation of the hatch body (1) from the retracted state to the unfolded state, the pedal (20) is subjected to rotational centrifugal force and rotates away from the hatch body (1) and eventually stops in a horizontal state.

4. The aircraft door and ladder system according to claim 3, characterized in that, When the pedal (20) is in a horizontal position, at least one side abuts against the inside of the hatch body (1).

5. The aircraft door and ladder system according to claim 4, characterized in that, The various pedals (20) are connected together by ropes (22).

6. The aircraft door and ladder system according to claim 1, characterized in that, It also includes a handrail mechanism (3), which unfolds to one side of the door body (1) when the door body (1) is in the unfolded state, so as to facilitate the user's grip, and folds into the aircraft and closes to the door body (1) when the door body (1) is in the retracted state.

7. The aircraft door and ladder system according to claim 6, characterized in that, The handrail mechanism (3) includes a first link (31) and a second link (32) that are rotatably connected to each other. The first link (31) is connected to the door body (1), and the second link (32) is connected to the aircraft (100).

8. The aircraft door and ladder system according to claim 7, characterized in that, The first link (31) includes a first straight rod (311) and a second straight rod (312) that are connected to each other, and the first straight rod (311) and the second straight rod (312) intersect at an obtuse angle.

9. The aircraft door and ladder system according to claim 1, characterized in that, The number of pedals (20) is 3.

10. An aircraft, characterized in that, Includes a door frame (4), an upper cabin door (5), and a door ladder system (6) as described in any one of claims 1-9, wherein the upper cabin door (5) and the door ladder system (6) are rotatably disposed within the door frame (4) to open or close the entrance (10) of the aircraft (100).

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