Aircraft tail electric air-drop cargo hold door

Abstract

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

Description

Technical Field

[0001] The present application belongs to the field of aircraft cabin doors, and in particular relates to an electric airdrop cargo door at the tail of an aircraft. Background Art

[0002] The airdrop cargo door provides a ground loading and unloading channel and an airdrop channel for the cargo in the aircraft cargo hold. The airdrop cargo door of the cargo aircraft often opens accidentally or cannot be opened because it bears the cargo load during the airdrop process. If the cargo door opens accidentally during the flight, it will cause the aircraft fuselage to depressurize and damage the fuselage structure, resulting in damage to the aircraft and casualties; if the door cannot be opened normally during the airdrop process, it will affect the execution of the airdrop mission.

[0003] Under the premise of meeting the requirements for opening and locking during airdrop, in order to prevent the cargo door from being accidentally opened during normal flight of the aircraft, the existing airdrop cargo door system is complex.

[0004] To this end, a kind of airdrop cargo door is needed to eliminate the above-mentioned problems. Summary of the invention

[0005] The purpose of the present application is to provide an electric airdrop cargo door at the rear of an aircraft to solve or alleviate at least one problem in the background technology.

[0006] The technical solution of the present application is: an electric airdrop cargo door at the rear of an aircraft, comprising:

[0007] A door body, the door body is hinged to a door mounting frame of the fuselage structure through a door hinge, a plurality of stop hook assemblies are provided on the edge of the door body, and the stop hook assemblies are connected to the fuselage structure when the airdrop cargo door is closed, so that the load of the airdrop cargo door is transferred and diffused to the fuselage structure through the door hinge and the stop hook assemblies;

[0008] A door electric actuator, one end of which is connected to the door body and the other end is connected to an actuator mounting frame of the fuselage structure, and is used to drive the door body to move and keep the door in the open position after the door is opened;

[0009] A guide assembly, the guide assembly being arranged at an edge of the door body and being used for guiding when the door body is closed or opened;

[0010] The locking mechanism is arranged on both sides of the door body away from the door hinge, and is used to lock the door body in a closed position when the door electric actuator closes the door body.

[0011] In an optional embodiment of the present application, the door body forms a load-bearing structure through a structural frame, long girders, and composite beams, and the load-bearing structure is covered with a skin to form an aerodynamic shape of the airdrop cargo door.

[0012] In an optional embodiment of the present application, there are two door hinges, thereby forming a movable pivot for the airdrop cargo door.

[0013] In an optional embodiment of the present application, a maintenance cover is provided on the hatch body.

[0014] In an optional embodiment of the present application, a sealing strip is provided on the edge of the door body.

[0015] In an optional embodiment of the present application, the stop hook assembly includes a stop hook 1, a stop hook support and a roller. The stop hook is in a semi-I-shape, one side of which is 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 achieve the locking of the airdrop cargo door.

[0016] In an optional embodiment of the present application, a single-side edge of the door body is provided with at least three stop hook assemblies, covering at least both ends and a middle portion of the single-side edge.

[0017] In an optional embodiment of the present application, the guide assembly includes 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 door body, and a guide roller is connected to its end, the guide roller is installed in the guide groove, and the guide roller can roll relative to the guide groove.

[0018] In an optional embodiment of the present application, the guide assembly further includes a limiting roller, which 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 an optional embodiment of the present application, the locking mechanism includes a lock electric actuator, a rocker arm, a retaining spring assembly, a pull rod and a lock hook. The lock electric actuator, rocker arm, retaining spring assembly and lock hook are respectively installed on the fuselage structure through pivoted supports, and the lock electric actuator, retaining spring assembly and pull rod are pivoted on the rocker arm, and the other end of the pull rod is connected to the lock hook. The lock hook can be driven to rotate by the lock electric actuator, thereby cooperating with the lock shaft on the lock hook support fixed on the door body to achieve locking of the door body and the fuselage structure.

[0020] In an optional embodiment of the present application, the retaining spring assembly includes 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 an optional embodiment of the present application, both ends of the pull rod are double-ear structures, and the double-ear structures at both ends are hinged to the rocker arm and the locking hook respectively.

[0022] The electric airdrop cargo door at the tail of the aircraft of the present application opens upward and inward to provide a loading and airdrop channel, which can effectively prevent the door from accidentally opening when the aircraft is flying, protect the safety of the aircraft and personnel, and improve the safety of the airdrop cargo door. The airdrop cargo door is automatically operated by an electric actuator, which is more suitable for use on all-electric aircraft, reducing the system composition of the aircraft. The stop hook assemblies arranged on both sides of the door body can transmit the aircraft load of the entire aircraft, reduce the deformation of the large opening of the door frame, and have obvious weight reduction advantages for the rear body of the fuselage. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0024] Figure 1 Shown is a schematic diagram of the airdrop cargo door composition of the present application.

[0025] Figure 2 This is a schematic diagram of the hatch lock mechanism in this application.

[0026] Figure 3 Schematic diagram of the guide assembly in this application.

[0027] Figure 4 Detailed schematic diagram of the guide assembly in this application.

[0028] Figure 5 Schematic diagram of the door stop hook assembly in this application.

[0029] Reference numerals:

[0030] 10-Body structure

[0031] 11-Hatch 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 arm, 252A-rocker arm support

[0045] 253-Retaining Spring Assembly, 253A-Retaining Spring Assembly Support

[0046] 254-Tie rod

[0047] 255-Lock Hook, 255A-Lock Hook Support

[0048] 256-Lock Axis

[0049] 26-Stop hook assembly

[0050] 261-Stop hook

[0051] 262-Stop hook support

[0052] 263-Roller

[0053] 27-Maintenance cover DETAILED DESCRIPTION

[0054] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.

[0055] The present application proposes an electric airdrop cargo door at the rear of an aircraft, which opens inward and upward to provide an airdrop channel and can effectively prevent the door from accidentally opening during flight, thus meeting the airworthiness safety requirements of the door.

[0056] like Figure 1 Shown is a schematic diagram of the overall structure of the electric airdrop cargo door at the rear of the aircraft provided by the present application. The airdrop cargo door 20 includes: a door body 21, a door electric actuator 23, a guide assembly 24, a locking mechanism 25 and a stop hook assembly 26.

[0057] The door body 21 is composed of a structural frame, a long stringer, a composite beam, etc., which constitute a load-bearing structure, and the skin is laid on the load-bearing structure to form the aerodynamic shape of the door. The door body 21 is hinged to the door mounting frame 11 of the fuselage structure 10 through a door hinge 22. In the present application, there are usually two door hinges 22 to form a rotation axis.

[0058] The edge of the door body 21 is provided with a plurality of stop hook assemblies 26, which are connected to the fuselage structure 10 when the airdrop cargo door 20 is closed, so that the load of the airdrop cargo door 20 is transferred and diffused to the fuselage structure 10 through the door hinge 22 and the stop hook assemblies 26. In some embodiments of the present application, three stop hook assemblies 26 are provided on a single side edge of the door body 21, which are respectively arranged at both ends and the middle of the single side edge.

[0059] like Figure 2 The figure shows a schematic diagram of the structure of the stop hook assembly 26 in the present application, wherein the stop hook assembly 26 includes a stop hook 261, a stop hook support 262 and a roller 263. The stop hook 261 is in a semi-I-shape, one side of which is fixed to the door body 21, the stop hook support 262 is fixed to the fuselage structure 10, and the roller 263 is installed on the stop hook support 262. When the airdrop cargo door 20 is closed, the other side of the stop hook 261 cooperates with the roller 263, thereby achieving the locking of the airdrop cargo door 20.

[0060] In some embodiments of the present application, a circle of sealing tape may be provided on the edge of the door body 21 to seal the airdrop cargo door 20 .

[0061] Furthermore, a maintenance cover 27 is provided on the hatch body 21 , and the maintenance cover 27 is usually arranged at approximately the middle position of the hatch body 21 .

[0062] The door electric actuator 23 is connected to the door body 21 and the actuator mounting frame 12 in the fuselage structure 10. The door electric actuator 23 can be used to flip the airdrop cargo door 20 inward and upward to open.

[0063] The guide assembly 24 is disposed on both sides of the door body 21 and is used to guide the door body 21 when the door electric actuator 23 retracts and extends the door body 21 .

[0064] like Figure 3 and Figure 4 The figure shows a schematic diagram of the structure of the guide assembly 24 in the present application, wherein the guide assembly 24 comprises a guide groove 241, a rotary rocker arm 242 and a guide roller 243. The guide groove 241 is fixed on the fuselage structure 10, and the rotary rocker arm 241 is rotatably arranged on the door body 21, and a guide roller 243 is connected to the end thereof, and the guide roller 243 is adapted to the guide groove 241. When the door electric actuator 23 drives the door body 21 to move, the guide roller 243 slides in the guide groove 241.

[0065] Furthermore, the guide assembly 24 also includes a limiting roller 244, which is arranged on the end surface 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 to ensure stable movement.

[0066] The locking mechanism 25 is arranged on both sides of the door body 21 away from the door hinge 22, and is used to lock the door body 21 in the closed position when the door electric actuator 23 closes the door body 21.

[0067] like Figure 5 The lock mechanism 25 of the present application is shown as a schematic diagram of the structure. The lock mechanism 25 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 connected to the fuselage structure 10 through a lock electric actuator support 251A, the rocker arm 252 is pivotally connected to the fuselage structure 10 through a rocker arm support 252A, and the retaining spring assembly 253 is pivotally connected to the fuselage structure 10 through a retaining spring assembly support. 253A is pivotally mounted on the fuselage structure 10, the lock hook 255 is pivotally mounted on the fuselage structure 10 through the 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 mounted on the lock hook 255. The lock electric actuator 251 drives the rocker arm 252 to rotate, and then the pull rod 254 can drive the lock hook 255 to move. The lock hook support 21A is arranged on the door body 21 at a position corresponding to the lock hook 255, and the lock hook support 21A is provided with a lock shaft 256, and when the lock hook 255 rotates, it can cooperate with the lock shaft 256 to achieve the locking of the door body 21 and the fuselage structure 10.

[0068] In the present application, the retaining spring assembly 253 includes a connecting shaft and a spring sleeved on the connecting shaft. When the lock electric actuator 251 drives the rocker arm 252 to rotate, the spring is compressed, which 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 hinged to the rocker arm 252 and the locking hook 255 respectively.

[0070] It should be noted that the above content of this application describes a single-sided airdrop cargo door, and the actual airdrop cargo door is a symmetrically arranged structure.

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

[0072] The electric airdrop cargo door at the tail of the aircraft of the present application opens upward and inward to provide a loading and airdrop channel, which can effectively prevent the door from accidentally opening when the aircraft is flying, protect the safety of the aircraft and personnel, and improve the safety of the airdrop cargo door. The airdrop cargo door is automatically operated by an electric actuator, which is more suitable for use on all-electric aircraft, reducing the system composition of the aircraft. The stop hook assemblies arranged on both sides of the door body can transmit the aircraft load of the entire aircraft, reduce the deformation of the large opening of the door frame, and have obvious weight reduction advantages for the rear body of the fuselage.

[0073] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. An electric airdrop cargo door at the tail of an aircraft, characterized in that: include: A door body, the door body is hinged to a door mounting frame of the fuselage structure through a door hinge, a plurality of stop hook assemblies are provided on the edge of the door body, and the stop hook assemblies are connected to the fuselage structure when the airdrop cargo door is closed, so that the load of the airdrop cargo door is transferred and diffused to the fuselage structure through the door hinge and the stop hook assemblies; A door electric actuator, one end of which is connected to the door body and the other end of which is connected to an actuator mounting frame of the fuselage structure, and is used to drive the door body to move; A guide assembly, the guide assembly being arranged at an edge of the door body and being used for guiding when the door body is closed or opened; The locking mechanism is arranged on both sides of the door body away from the door hinge, and is used to lock the door body in a closed position when the door electric actuator closes the door body.

2. The electric airdrop cargo door at the rear of an aircraft as claimed in claim 1, characterized in that: The door body is composed of a load-bearing structure consisting of a structural frame, long girders, and composite beams, and a skin is applied outside the load-bearing structure to form an aerodynamic shape of the airdrop cargo door.

3. The electric airdrop cargo door at the rear of an aircraft as claimed in claim 1, characterized in that: The door has two hinges, thereby forming a movable rotating shaft for the airdrop cargo door.

4. The electric airdrop cargo door at the rear of an aircraft as claimed in claim 2 or 3, characterized in that: A maintenance cover is provided on the hatch body.

5. The electric airdrop cargo door at the rear of an aircraft as claimed in claim 4, characterized in that: A sealing strip is provided at the edge of the door body.

6. The electric airdrop cargo door at the rear of an aircraft as claimed in claim 1, characterized in that: The stop hook assembly includes a stop hook 1, a stop hook support and a roller. The stop hook is in a semi-I-shape, one side of which is 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 achieve the transfer of the load of the airdrop cargo door closing position.

7. The electric airdrop cargo door at the rear of an aircraft as claimed in claim 6, characterized in that: The single-side edge of the door body is provided with at least three stop hook components, which at least cover the two ends and the middle of the single-side edge.

8. The electric airdrop cargo door at the rear of an aircraft as claimed in claim 1, characterized in that: The guide assembly includes 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 door body, and a guide roller is connected to the end thereof. The guide roller is installed in the guide groove, and the guide roller can roll relative to the guide groove.

9. The electric airdrop cargo door at the rear of an aircraft as claimed in claim 8, characterized in that: The guide assembly further includes a limiting roller, which is arranged on the end surface 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 electric airdrop cargo door at the rear of an aircraft as claimed in claim 1, characterized in that: The locking mechanism includes an electric lock actuator, a rocker arm, a retaining spring assembly, a pull rod and a lock hook. The electric lock actuator, the rocker arm, the retaining spring assembly and the lock hook are respectively installed on the fuselage structure through pivoted supports, and the electric lock actuator, the retaining spring assembly and the pull rod are pivotally connected to the rocker arm. The other end of the pull rod is connected to the lock hook. The lock hook can be driven to rotate by the electric lock actuator, thereby cooperating with the lock shaft on the lock hook support fixed on the door body to achieve locking of the door body and the fuselage structure.

11. The electric airdrop cargo door at the rear of an aircraft as claimed in claim 10, characterized in that: The retaining spring assembly includes 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.

12. The electric airdrop cargo door at the rear of an aircraft as claimed in claim 10, characterized in that: Both ends of the pull rod are double-ear structures, and the double-ear structures at both ends are hinged to the rocker arm and the lock hook respectively.

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