Electrically powered tail airdrop cargo door for an aircraft

Abstract

The application provides an airplane tail electric air-drop cargo hatch door, and belongs to the technical field of airplane hatch doors. The air-drop cargo hatch door comprises a hatch door body, the hatch door body is hinged to a hatch door mounting frame of a fuselage structure through a hatch door hinge, the edge of the hatch door body is provided with a plurality of stop hook assemblies, the stop hook assemblies are connected to the fuselage structure when the air-drop cargo hatch door is closed, so that the load of the air-drop cargo hatch door is transmitted and diffused to the fuselage structure through the hatch door hinge and the stop hook assemblies; a hatch door electric actuator, one end of the hatch door electric actuator is connected to the hatch door body, the other end of the hatch door electric actuator is connected to an actuator mounting frame of the fuselage structure, and the hatch door electric actuator is used for driving the hatch door body to move; a guide assembly, the guide assembly is arranged at the edge of the hatch door body and is used for guiding when the hatch door body is closed or opened; and a lock mechanism, the lock mechanism is arranged on both sides of the hatch door body away from the hatch door hinge and is used for locking in a closed position when the hatch door electric actuator closes the hatch door body.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of aircraft cargo doors, and particularly relates to an electrically-operated air-drop cargo door at the tail of an aircraft. BACKGROUND

[0002] The air-drop cargo door provides a ground loading and unloading passage and an air-drop passage for the cargo in the cargo hold of an aircraft. The air-drop cargo door of a cargo aircraft often fails to open or cannot be opened due to the load of the cargo during air-drop. If the cargo hold door is accidentally opened during flight, the aircraft fuselage will be depressurized, the fuselage structure will be damaged, and the aircraft will be damaged and personnel will be injured. If the cargo hold door cannot be normally opened during air-drop, the air-drop task will be affected.

[0003] In order to prevent the cargo hold door from being accidentally opened during normal flight of the aircraft, the existing air-drop cargo door system is complex.

[0004] Therefore, an air-drop cargo door is needed to eliminate the above problems. SUMMARY

[0005] The present application aims to provide an electrically-operated air-drop cargo door at the tail of an aircraft to solve or alleviate at least one problem in the background art.

[0006] The technical solution of the present application is: an electrically-operated air-drop cargo door at the tail of an aircraft, comprising:

[0007] a door body, which is hinged to a door mounting frame of a fuselage structure through a door hinge, and the edge of the door body is provided with a plurality of stop hook assemblies, which are connected to the fuselage structure when the air-drop cargo door is closed, so that the load of the air-drop cargo door is transmitted and diffused to the fuselage structure through the door hinge and the stop hook assemblies;

[0008] a door electric actuator, which is connected to the door body at one end and connected to an actuator mounting frame of the fuselage structure at the other end, for driving the door body to move and keeping the door body in the open position after the door is opened;

[0009] a guide assembly, which is arranged at the edge of the door body, for guiding the door body when the door body is closed or opened;

[0010] a lock mechanism, which is arranged on both sides of the door body away from the door hinge, for locking in the closed position when the door body is closed by the door electric actuator.

[0011] In an optional embodiment of the present application, the door body is composed of a load-bearing structure formed by a structural frame, a stringer and a composite beam, and a skin is arranged outside the load-bearing structure to form the aerodynamic shape of the air-drop cargo door.

[0012] In optional embodiments of the present application, the hatch hinge is two, thereby forming a movable pivot of the air-drop cargo hatch door.

[0013] In optional embodiments of the present application, the hatch body is provided with a maintenance cover.

[0014] In optional embodiments of the present application, the edge of the hatch body is provided with a sealing strip.

[0015] In optional embodiments of the present application, the stop hook assembly comprises a stop hook 1, a stop hook support and a roller, the stop hook is in a half I shape, one side of which is fixed with the hatch body, the stop hook support is fixed on the fuselage structure, and the roller is installed on the stop hook support. When the air-drop cargo hatch door is closed, the other side of the stop hook cooperates with the roller, thereby realizing the locking of the air-drop cargo hatch door.

[0016] In optional embodiments of the present application, the single-side edge of the hatch body is provided with at least three stop hook assemblies, covering at least two ends and the middle part of the single-side edge.

[0017] In optional embodiments of the present application, the guide assembly comprises a guide groove, a rotating rocker arm and a guide roller, the guide groove is fixed on the fuselage structure, the rotating rocker arm is rotatably arranged on the hatch body, the end thereof is connected with the guide roller, the guide roller is installed in the guide groove, and the guide roller can roll relative to the guide groove.

[0018] In optional embodiments of the present application, the guide assembly further comprises a limiting roller, the limiting roller is arranged on the end face of the guide roller, the guide roller rolls relative to the side wall of the guide groove, and the limiting roller rolls relative to the bottom surface of the guide groove.

[0019] In optional embodiments of the present application, the lock mechanism comprises a lock electric actuator, a rocker arm, a retaining spring assembly, a pull rod and a lock hook, the lock electric actuator, the rocker arm, the retaining spring assembly and the lock hook are respectively installed on the fuselage structure through the pivoted supports, and the lock electric actuator, the retaining spring assembly and the pull rod are pivoted on the rocker arm, the other end of the pull rod is connected with the lock hook, the lock hook can be driven to rotate by the lock electric actuator, thereby cooperating with the lock shaft fixed on the lock hook support of the hatch body, realizing the locking of the hatch body and the fuselage structure.

[0020] In optional embodiments of the present application, the retaining spring assembly comprises a connecting shaft and a spring sleeved on the connecting shaft, when the lock electric actuator drives the rocker arm to rotate, the spring is compressed to provide a restoring force to the rocker arm.

[0021] In optional embodiments of the present application, both ends of the pull rod are double-ear structures, and the double-ear structures at both ends are respectively hinged with the rocker arm and the lock hook.

[0022] The upwardly inwardly opening aircraft tail electric airdrop cargo door of the application provides a loading and airdrop channel, can effectively prevent the door from being accidentally opened when the aircraft is flying, protects the safety of the aircraft and personnel, and improves the safety of the airdrop cargo door. The airdrop cargo door is automatically controlled by an electric actuator, is more suitable for use on an all-electric aircraft, reduces the system composition of the aircraft, and the stop hook assembly arranged on both sides of the door body can transmit the load of the aircraft, reduce the deformation of the large opening of the door frame, and has obvious weight reduction advantage for the rear body of the aircraft. BRIEF DESCRIPTION OF DRAWINGS

[0023] In order to more clearly illustrate the technical solutions provided by the application, the following will briefly introduce the drawings. Obviously, the drawings described below are only some embodiments of the application.

[0024] Figure 1 The figure shows the composition of the airdrop cargo door of the application.

[0025] Figure 2 The figure shows the composition of the door lock mechanism in the application.

[0026] Figure 3 The figure shows the guide assembly in the application.

[0027] Figure 4 The figure shows the details of the guide assembly in the application.

[0028] Figure 5 The figure shows the door stop hook assembly in the application.

[0029] Reference signs:

[0030] 10-aircraft body structure

[0031] 11-door mounting frame

[0032] 12-actuator mounting frame

[0033] 20-airdrop cargo door

[0034] 21-door body, 21A-lock hook support

[0035] 22-door hinge

[0036] 23-door electric actuator

[0037] 24-guide assembly

[0038] 241-guide groove

[0039] 242-rotary rocker arm

[0040] 243-guide roller

[0041] 244-limiting roller

[0042] 25-lock mechanism

[0043] 251-lock electric actuator, 251A-lock electric actuator support

[0044] 252-rocker, 252A-rocker support

[0045] 253-retention spring assembly, 253A-retention spring assembly support

[0046] 254-pull rod

[0047] 255-lock hook, 255A-lock hook support

[0048] 256-lock shaft

[0049] 26-stop hook assembly

[0050] 261-stop hook

[0051] 262-stop hook support

[0052] 263-roller

[0053] 27-maintenance access cover DETAILED DESCRIPTION

[0054] In order to make the purpose, technical scheme and advantages of the present application clearer, the technical scheme of the present application will be described in more detail below in combination with the drawings in the embodiments of the present application.

[0055] The present application provides an airplane tail electric air-drop cargo hatch door, which opens inward and upward to provide an air-drop passage and effectively prevents accidental opening of the hatch door in flight, meeting the airworthiness safety requirements of the hatch door.

[0056] As Figure 1 The present application provides an airplane tail electric air-drop cargo hatch door, which opens inward and upward to provide an air-drop passage and effectively prevents accidental opening of the hatch door in flight, meeting the airworthiness safety requirements of the hatch door.

[0057] The hatch door body 21 is composed of a load-bearing structure of structural frames, stringers and composite beams, and a skin is laid on the load-bearing structure to form the aerodynamic shape of the hatch door. The hatch door body 21 is hinged to the hatch door mounting frame 11 of the fuselage structure 10 through the hatch door hinge 22. In the present application, the hatch door hinge 22 is usually two, thereby forming a rotation axis.

[0058] The edge of the hatch body 21 is provided with a plurality of stop hook assemblies 26, which are connected with the fuselage structure 10 when the air-drop cargo hatch door 20 is closed, so as to transmit and diffuse the load of the air-drop cargo hatch door 20 to the fuselage structure 10 through the hatch hinge 22 and the stop hook assembly 26. In some embodiments of the present application, the single-side edge of the hatch body 21 is provided with three stop hook assemblies 26, which are respectively arranged at the two ends and the middle of the single-side edge.

[0059] As shown in Figure 2 The stop hook assembly 26 in the present application is shown in the structural schematic diagram, which comprises a stop hook 261, a stop hook support 262 and a roller 263. The stop hook 261 is in the shape of a half I-beam, one side of which is fixed with the hatch body 21, the stop hook support 262 is fixed on the fuselage structure 10, and the roller 263 is installed on the stop hook support 262. When the air-drop cargo hatch door 20 is closed, the other side of the stop hook 261 cooperates with the roller 263, so as to realize the locking of the air-drop cargo hatch door 20.

[0060] In some embodiments of the present application, a sealing strip can be arranged on the edge of the hatch body 21, which is used for sealing the air-drop cargo hatch door 20.

[0061] Further, the hatch body 21 is provided with a maintenance door cover 27, which is usually arranged at the middle of the hatch body 21.

[0062] The hatch electric actuator 23 is connected between the hatch body 21 and the actuator mounting frame 12 in the fuselage structure 10, and the air-drop cargo hatch door 20 can be turned upward and opened inward through the hatch electric actuator 23.

[0063] The guide assembly 24 is arranged on both sides of the hatch body 21, which is used for guiding the hatch body 21 during the opening and closing process of the hatch body 21 by the hatch electric actuator 23.

[0064] As shown in Figure 3 and Figure 4 The guide assembly 24 in the present application is shown in the structural schematic diagram, which comprises a guide groove 241, a rotating rocker arm 242 and a guide roller 243. The guide groove 241 is fixed on the fuselage structure 10, the rotating rocker arm 242 is rotatably arranged on the hatch body 21, and the end thereof is connected with the guide roller 243, which is adapted to the guide groove 241. When the hatch electric actuator 23 drives the hatch body 21 to move, the guide roller 243 slides in the guide groove 241.

[0065] Further, the guide assembly 24 further comprises a limiting roller 244, which is arranged on the end face of the guide roller 243. The guide roller 243 slides relative to the side wall of the guide groove 241, and the limiting roller 244 slides relative to the bottom surface of the guide groove 241, so as to ensure the stability of the movement.

[0066] Lock mechanisms 25 are arranged on both sides of the cabin door body 21 away from the cabin door hinge 22, and are used to lock in the closed position when the cabin door electric actuator 23 closes the cabin door body 21.

[0067] As Figure 5 The lock mechanism 25 in the present application is shown in the structural schematic diagram, which includes a lock electric actuator 251, a rocker arm 252, a retaining spring assembly 253, a pull rod 254, and a lock hook 255. The lock electric actuator 251 is pivotally arranged on the fuselage structure 10 through a lock electric actuator support 251A, the rocker arm 252 is pivotally arranged on the fuselage structure 10 through a rocker arm support 252A, the retaining spring assembly 253 is pivotally arranged on the fuselage structure 10 through a retaining spring assembly support 253A, the lock hook 255 is pivotally arranged on the fuselage structure 10 through a lock hook support 255A, and the lock electric actuator 251, the retaining spring assembly 253, and the pull rod 254 are all connected to the rocker arm 252 (the lock electric actuator support 251A, the retaining spring assembly support 253A, the rocker arm support 252A, and the lock hook support 255A are on the same plane), and the pull rod 254 is pivotally connected to the lock hook 255. The rocker arm 252 is driven to rotate by the lock electric actuator 251, and then the pull rod 254 drives the lock hook 255 to move. A lock hook support 21A is arranged on the cabin door body 21 corresponding to the position of the lock hook 255, and a lock shaft 256 is arranged on the lock hook support 21A, so that the lock hook 255 can cooperate with the lock shaft 256 to realize the locking of the cabin door body 21 and the fuselage structure 10 when the lock hook 255 rotates.

[0068] In the present application, the retaining spring assembly 253 includes a connecting shaft and a spring sleeved on the connecting shaft. When the rocker arm 252 is driven to rotate by the lock electric actuator 251, the spring is compressed, and it provides a restoring force to the rocker arm 252.

[0069] In some embodiments of the present application, both ends of the pull rod 254 are double-ear structures, and the double-ear structures at both ends are hingedly connected to the rocker arm 252 and the lock hook 255, respectively.

[0070] It should be noted that the above description of the present application is for a single-side air-drop cargo cabin door, and the actual air-drop cargo cabin door is a symmetrically arranged structure.

[0071] The opening process of the air-drop cargo cabin door 20 of the present application is as follows: the lock electric actuator 251 opens the lock mechanism, the cabin door electric actuator 23 drives the cabin door body 21 to open upward and inward, and the cabin door body 21 is kept in the open position by the cabin door electric actuator 23; the cabin door closing process is opposite to the opening process.

[0072] The aircraft tail electric airdrop cargo hatch door opens upward and inward to provide a loading and airdrop channel, which can effectively prevent the hatch door from being accidentally opened when the aircraft is flying, protect the safety of the aircraft and personnel, and improve the safety of the airdrop cargo hatch door. The airdrop cargo hatch door is automatically controlled by an electric actuator, which is more suitable for use on an all-electric aircraft, reduces the system composition of the aircraft, and the stop hook assembly arranged on both sides of the hatch door body can transmit the load of the aircraft, reduce the deformation of the large opening of the hatch door frame, and has obvious weight reduction advantage for the rear body of the aircraft.

[0073] The above is only a specific embodiment of the present application, but the protection scope of the present application is not limited thereto, any person skilled in the art can easily think of changes or replacements within the technical range disclosed in the present application, which should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. An electrically operated cargo door at the tail of an aircraft, characterized in that, include: The door body is hinged to the door mounting frame of the fuselage structure via a door hinge. The edge of the door body is provided with multiple stop hook assemblies. The stop hook assemblies are connected to the fuselage structure when the airdrop cargo door is closed, thereby transferring and distributing the load of the airdrop cargo door to the fuselage structure through the door hinge and the stop hook assemblies. A hatch electric actuator, wherein one end of the hatch electric actuator is connected to the hatch body and the other end is connected to the actuator mounting frame of the fuselage structure, and is used to drive the hatch body to move; A guide assembly is disposed on the edge of the hatch body and is used to guide the hatch body when it is closed or opened; A locking mechanism is provided on both sides of the hatch body away from the hatch hinge. This mechanism locks the hatch body in the closed position when the hatch electric actuator closes it. The locking mechanism includes a locking electric actuator, a rocker arm, a retaining spring assembly, a pull rod, and a locking hook. These components are pivotally mounted on the fuselage structure via supports. The locking electric actuator, retaining spring assembly, and pull rod are pivotally connected to the rocker arm. The other end of the pull rod is connected to the locking hook. The locking electric actuator drives the locking hook to rotate, thereby engaging with a locking shaft fixed to the locking hook support on the hatch body to lock the hatch body to the fuselage structure. The retaining spring assembly includes a connecting shaft and a spring sleeved on the connecting shaft. When the locking electric actuator drives the rocker arm to rotate, the spring is compressed, providing a restoring force to the rocker arm.

2. The electrically operated tail cargo door of an aircraft as described in claim 1, characterized in that, The door body is constructed by a structural frame, stringers, and composite beams to form a load-bearing structure. The load-bearing structure is covered with a skin to form the aerodynamic shape of the airdrop cargo door.

3. The electrically operated tail cargo door of an aircraft as described in claim 1, characterized in that, The hatch has two hinges, forming a movable pivot for the airdrop cargo hatch.

4. The electrically operated tail cargo door of an aircraft as described in claim 2 or 3, characterized in that, The hatch body is equipped with a maintenance cover.

5. The electrically operated tail cargo door of an aircraft as described in claim 4, characterized in that, The edges of the hatch body are equipped with sealing strips.

6. The electrically operated tail-mounted cargo door of an aircraft as described in claim 1, characterized in that, The stop hook assembly includes a stop hook, a stop hook support, and a roller. The stop hook is in the shape of a semi-I-beam, with one side fixed to the door body. The stop hook support is fixed to the fuselage structure, and the roller is installed on the stop hook support. When the airdrop cargo door is closed, the other side of the stop hook cooperates with the roller to realize the transfer of load at the closed position of the airdrop cargo door.

7. The electrically operated tail cargo door of an aircraft as described in claim 6, characterized in that, The hatch body has at least three stop hook assemblies on one side edge, covering at least both ends and the middle of the one side edge.

8. The electrically operated tail-mounted cargo door of an aircraft as described in claim 1, characterized in that, The guiding assembly includes a guide groove, a rotating rocker arm, and a guide roller. The guide groove is fixed to the fuselage structure. The rotating rocker arm is rotatably mounted on the door body, and its end is connected to a guide roller. The guide roller is installed in the guide groove and can roll relative to the guide groove.

9. The electrically operated tail cargo door of an aircraft as described in claim 8, characterized in that, The guide assembly also includes a limiting roller, which is disposed on the end face of the guide roller. The guide roller rolls relative to the side wall of the guide groove, and the limiting roller rolls relative to the bottom surface of the guide groove.

10. The electrically operated tail cargo door of an aircraft as described in claim 1, characterized in that, Both ends of the pull rod have a double-ear structure, and the double-ear structure at both ends is hinged to the rocker arm and the locking hook, respectively.

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