An aircraft electric hoist guide rail butt joint device and method

Abstract

The present application belongs to the technical field of aircraft cargo hoisting equipment, and provides an aircraft electric hoist guide rail butt joint device and method. Through the action of a linear actuator and a connecting rod, the butt joint guide rail moves along a fixed track, realizing butt joint and separation with the rear cargo door fixed guide rail and the cargo compartment tail end fixed guide rail. After the butt joint work is completed, the electric hoist hoisted cargo can move from the cargo compartment to the aircraft tail door, and vice versa. After the butt joint guide rail is lifted, it does not hinder the execution of the closing or opening action instruction of the rear cargo door.

Description

Technical Field

[0001] This invention belongs to the field of mechanical technology of aircraft cargo hoisting equipment, specifically referring to a guide rail docking device and method for aircraft electric cranes. Background Technology

[0002] When a transport aircraft's mission system is equipped with an electric crane, crane rails are typically installed inside the aircraft's cargo hold, allowing the electric crane to move along these rails. For rails installed at the rear cargo door, a docking device is required to align the rail at the rear cargo door with a fixed rail inside the cargo hold when the rear cargo door is fully open. The device should ensure that disengaging from the docking rail does not affect the closure of the rear cargo door.

[0003] The guide rail docking devices designed for foreign transport aircraft hoisting systems are only used for docking the fixed guide rails of the aft cargo door. Since only one section of the guide rail needs to be docked, the docking can be completed with simple translation. If it is necessary to dock the guide rail at the rear cargo door with the two sections of the fixed guide rail at the stern of the cargo hold, a more complex guide rail docking device is required to complete the docking of the two sections of the guide rail. Summary of the Invention

[0004] The purpose of this invention is to address the shortcomings of existing technologies by providing an aircraft electric crane guide rail docking device and method for docking a fixed guide rail at the rear cargo door and a fixed guide rail at the tail end of the cargo hold. After docking is completed, the electric crane can move from inside the cargo hold to the rear door of the transport aircraft, and vice versa. After the docking guide rail is raised, the aircraft tail door can be closed or opened.

[0005] The technical solution of the present invention: In order to achieve the above objectives, according to the first aspect of the present invention, an aircraft electric crane guide rail docking device is proposed, comprising a fixed bracket (1), a first linear actuation mechanism (2), a second linear actuation mechanism (3), a third linear actuation mechanism (4), an auxiliary telescopic mechanism, a control box (7), and a docking guide rail (8).

[0006] One side of the fixed bracket (1) is fixedly installed on the frame structure of the transport machine. The first linear actuator (2) and the second linear actuator (3) are respectively arranged in a relatively parallel and symmetrical position on the other side of the fixed bracket (1). One end of the first linear actuator (2) is the output shaft (2a) of the first linear actuator, and the other end is the fixed end of the first linear actuator. The output shaft (2a) of the first linear actuator is rotatably connected to the docking guide rail (8), and the fixed end of the first linear actuator is rotatably connected to the fixed bracket (1). One end of the second linear actuator (3) is the output shaft (3a) of the second linear actuator, and the other end is the fixed end of the second linear actuator. The output shaft (3a) of the second linear actuator is rotatably connected to the docking guide rail (8). The second linear actuator is rotatably connected to the fixed bracket (1); the auxiliary telescopic mechanism includes multiple interconnected connecting rods, one end of which is rotatably connected to the fixed bracket (1), and the other end is rotatably connected to the docking guide rail (8); one end of the third linear actuator (4) is the output shaft (4a) of the third linear actuator, and the other end is the fixed end of the third linear actuator, the fixed end of which is rotatably connected to the docking guide rail (8), and the output shaft (4a) of the third linear actuator is rotatably connected to a connecting rod in the auxiliary telescopic mechanism; the control box (7) is communicatively connected to the first linear actuator (2), the second linear actuator (3), and the third linear actuator (4).

[0007] In one possible embodiment, the auxiliary telescopic mechanism includes a first link (5) and a second link (6). One end of the first link (5) is hinged to the docking guide rail (8), and the other end is hinged to the second link (6). The other end of the second link (6) is hinged to the fixed bracket (1). The output shaft (4a) of the third linear actuation mechanism is rotatably connected to the first link (5).

[0008] In one possible embodiment, a proximity switch is installed on the docking guide rail (8) to detect whether the docking guide rail (8) is flush with the fixed guide rails on both sides. The proximity switch is communicatively connected to the control box (7).

[0009] In one possible embodiment, the first linear actuator (2), the second linear actuator (3), and the third linear actuator (4) are equipped with linear displacement sensors, which can feed back the positions of the first linear actuator output shaft (2a), the second linear actuator output shaft (3a), and the third linear actuator output shaft (4a) to the control box (7).

[0010] In one possible embodiment, the first linear actuator (2), the second linear actuator (3), and the third linear actuator (4) have a self-locking function.

[0011] In one possible embodiment, the control box (7) is mounted on the fixed bracket (1).

[0012] According to a second aspect of the present invention, a method for docking an aircraft electric crane guide rail is proposed. The above-mentioned aircraft electric crane guide rail docking device is used, and the first linear actuator (2), the second linear actuator (3), and the third linear actuator (4) are coordinated by the control box (7) to make the docking guide rail (8) dock flush with the fixed guide rails on both sides or dock and separate from the fixed guide rails on both sides.

[0013] In one possible embodiment, the specific process by which the control box (7) controls the docking guide rail (8) to dock and separate from the fixed guide rails on both sides is as follows: the control box (7) controls the first linear actuator output shaft (2a) and the second linear actuator output shaft (3a) to retract simultaneously at the same speed, the third linear actuator (4) remains self-locking, and the docking guide rail (8) moves vertically upward; when the first linear actuator (2) and the second linear actuator (3) have both retracted to their limit positions, the internal sensors... The device transmits the signal to the control box (7), which controls the first linear actuator (2) and the second linear actuator (3) to stop working and remain self-locked. The control box (7) controls the output shaft (4a) of the third linear actuator to extend. The first linear actuator (2) and the second linear actuator (3) remain self-locked. The docking guide rail (8) is docked and separated from the fixed guide rails on both sides under the action of the output shaft (4a) of the third linear actuator, without hindering the closing or opening of the aircraft tail door.

[0014] In one possible embodiment, the specific process by which the control box (7) controls the docking guide rail (8) to dock flush with the fixed guide rails on both sides is as follows: The control box (7) controls the output shaft (4a) of the third linear actuator to retract. When the output shaft (4a) of the third linear actuator retracts to the limit position, the internal sensor transmits a signal to the control box (7). The control box (7) controls the third linear actuator (4) to stop working and remain self-locked. The control box (7) controls the output shaft (2a) of the first linear actuator and the output shaft (3a) of the second linear actuator to extend at the same speed, driving the docking guide rail (8) to move vertically downward. When it docks flush with the fixed guide rails on both sides, the output shaft (2a) of the first linear actuator and the output shaft (3a) of the second linear actuator stop moving and remain self-locked.

[0015] The beneficial effects of this invention are as follows: This invention provides a docking device for an electric crane in an aircraft cargo hold. Through the action of a linear actuation mechanism and a connecting rod, the docking guide rail moves along a fixed trajectory, achieving docking and separation with the fixed guide rails at the rear cargo door and the tail end of the cargo hold. After docking is completed, the electric crane can move cargo from inside the cargo hold to the aircraft's tail door, and vice versa. Raising the docking guide rail does not obstruct the rear cargo door from performing closing or opening commands. Attached Figure Description

[0016] Figure 1 This is the front view of the electric crane guide rail docking device after it has been aligned.

[0017] Figure 2 This is the front view of the electric crane guide rail docking device after docking and separation. Detailed Implementation

[0018] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention.

[0019] like Figure 1 As shown, an aircraft electric crane guide rail docking device includes: a fixed bracket (1), a first linear actuator (2), a second linear actuator (3), a third linear actuator (4), a first link (5), a second link (6), a control box (7), and a docking guide rail (8);

[0020] The fixed bracket (1) is fixedly installed on the frame structure of the transport machine. The first linear actuator output shaft (2a) of the first linear actuator (2) is hinged to the joint on the fixed bracket (1), and the other end joint is hinged to the joint on the docking guide rail (8). The second linear actuator output shaft (3a) of the second linear actuator (3) is hinged to the joint on the fixed bracket (1), and the other end joint is hinged to the joint on the docking guide rail (8). The third linear actuator output shaft (4a) of the third linear actuator (4) is hinged to the joint on the first connecting rod (5), and the other end joint is hinged to the joint on the docking guide rail (8). One end of the first connecting rod (5) is hinged to the docking guide rail (8), and the other end is hinged to the second connecting rod (6). The other end of the second connecting rod (6) is hinged to the fixed bracket (1).

[0021] In one possible embodiment, the first linear actuator (2), the second linear actuator (3), and the third linear actuator (4) are equipped with linear displacement sensors, which can provide feedback to the control box (7) on the positions of the output shafts (2a), (3a), and (4a) of the first linear actuator, the second linear actuator, and the third linear actuator.

[0022] In one possible embodiment, the first linear actuator (2), the second linear actuator (3), and the third linear actuator (4) have a self-locking function. When the docking guide rail (8) is fully aligned with the cargo hold tail end fixed guide rail and the rear cargo hold door fixed guide rail, the first linear actuator (2), the second linear actuator (3), and the third linear actuator (4) remain self-locked.

[0023] In one possible embodiment, the control box (7) can control the first linear actuator (2), the second linear actuator (3), and the third linear actuator (4) to work in different sequences.

[0024] In one possible embodiment, the control box (7) is mounted on the fixed bracket (1).

[0025] A method for docking guide rails of an aircraft electric crane, wherein the control box (7) controls the docking guide rail (8) to dock and separate from the fixed guide rails on both sides. The specific process is as follows: the guide rail docking device is in the position of Figure 1In the current state, the docking guide rail (8) is fully aligned with the cargo hold tail end fixed guide rail one and cargo hold tail end fixed guide rail two. The control box (7) controls the first linear actuator (2), the first linear actuator output shaft (2a), the second linear actuator (3), and the second linear actuator output shaft (3a) to retract simultaneously at the same speed. The third linear actuator (4) remains self-locked, and the docking guide rail (8) moves vertically upward. When the first linear actuator (2) and the second linear actuator (3) retract to their limit positions, the internal sensors transmit signals to the control box (7). The control box (7) controls the first linear actuator (2) and the second linear actuator (3) to stop working and remain self-locked. The control box (7) controls the linear actuator (4) and the third linear actuator output shaft (4a) to extend. The first linear actuator (2) and the second linear actuator (3) remain self-locked, and the docking guide rail (8) moves to the position under the action of the third linear actuator output shaft (4a). Figure 2 The position shown does not obstruct the closing or opening of the aircraft's rear door.

[0026] The specific process by which the control box (7) controls the docking guide rail (8) to be aligned with the fixed guide rails on both sides is as follows: the guide rail docking device is in the position of Figure 2 In the state, the control box (7) controls the third linear actuator (4) and the output shaft (4a) of the third linear actuator to retract. When the linear actuator (4) and the output shaft (4a) of the third linear actuator retract to the limit position, the internal sensor transmits a signal to the control box (7), and the control box (7) controls the third linear actuator (4) to stop working and maintain self-locking. The control box (7) controls the first linear actuator (2) and the output shaft (2a) of the first linear actuator and the second linear actuator (3) and the output shaft (3a) of the second linear actuator to extend at the same speed, driving the docking guide rail (8) to move vertically downward. A proximity switch is installed on the docking guide rail (8). When the proximity switch detects the docking guide rail to be in position, the first linear actuator (2) and the output shaft (2a) of the first linear actuator and the output shaft (3a) of the second linear actuator (3) stop moving and maintain self-locking. The guide rail docking device is in Figure 1 state.

Claims

1. An aircraft electric trolley rail docking device, characterized in that, It comprises a fixed support (1), a first linear actuator (2), a second linear actuator (3), a third linear actuator (4), an auxiliary telescopic mechanism, a control box (7), and a docking guide rail (8). The fixed support (1) is fixedly installed on one side of the frame structure of the conveyor, the first linear actuator (2) and the second linear actuator (3) are respectively arranged on the other side of the fixed support (1) at opposite parallel and symmetrical positions, one end of the first linear actuator (2) is a first linear actuator output shaft (2a), and the other end is a first linear actuator fixed end, the first linear actuator output shaft (2a) is rotatably connected with the docking guide rail (8), and the first linear actuator fixed end is rotatably connected with the fixed support (1); one end of the second linear actuator (3) is a second linear actuator output shaft (3a), and the other end is a second linear actuator fixed end, the second linear actuator output shaft (3a) is rotatably connected with the docking guide rail (8), and the second linear actuator fixed end is rotatably connected with the fixed support (1); the auxiliary telescopic mechanism comprises a plurality of segments of hingedly connected connecting rods, one end of the auxiliary telescopic mechanism is rotatably connected with the fixed support (1), and the other end is rotatably connected with the docking guide rail (8); one end of the third linear actuator (4) is a third linear actuator output shaft (4a), and the other end is a third linear actuator fixed end, the third linear actuator fixed end is rotatably connected with the docking guide rail (8), and the third linear actuator output shaft (4a) is rotatably connected with one segment of the connecting rods of the auxiliary telescopic mechanism; the auxiliary telescopic mechanism comprises a first connecting rod (5) and a second connecting rod (6), one end of the first connecting rod (5) is hingedly connected with the docking guide rail (8), the other end is hingedly connected with the second connecting rod (6), and the other end of the second connecting rod (6) is hingedly connected with the fixed support (1); the third linear actuator output shaft (4a) is rotatably connected with the first connecting rod (5); the control box (7) is in communication connection with the first linear actuator (2), the second linear actuator (3), and the third linear actuator (4).

2. An aircraft electric trolley rail docking device according to claim 1, wherein, A proximity switch is installed on the docking guide rail (8) and used for detecting whether the docking guide rail (8) is flush with the two side fixed guide rails, and the proximity switch is in communication connection with the control box (7).

3. An aircraft electric overhead crane rail docking device as claimed in claim 1, wherein, The first linear actuator (2), the second linear actuator (3), and the third linear actuator (4) are internally provided with linear displacement sensors, which can feed back the positions of the first linear actuator output shaft (2a) of the first linear actuator, the second linear actuator output shaft (3a) of the second linear actuator, and the third linear actuator output shaft (4a) of the third linear actuator to the control box (7).

4. An aircraft electric trolley rail docking device as claimed in claim 1, wherein, The first linear actuator (2), the second linear actuator (3), and the third linear actuator (4) have a self-locking function.

5. An aircraft electric trolley rail docking device as claimed in claim 1, wherein, The control box (7) is installed on the fixed support (1).

6. A method of interfacing the guide rails of an electric aircraft trolley according to any one of claims 1 to 5, characterized in that, The control box (7) cooperatively controls the first linear actuator (2), the second linear actuator (3) and the third linear actuator (4) to make the docking guide rail (8) flush with the two side fixed guide rails or separate from the two side fixed guide rails.

7. A method of butt joining the rails of an electric trolley jib crane on an aircraft as claimed in claim 6 wherein, The specific process of the control box (7) controlling the docking guide rail (8) to separate from the two side fixed guide rails is as follows: the control box (7) controls the first linear actuator output shaft (2a) of the first linear actuator and the second linear actuator output shaft (3a) of the second linear actuator to be withdrawn at the same speed at the same time, the third linear actuator (4) remains self-locking, and the docking guide rail (8) moves vertically upward; when the first linear actuator (2) and the second linear actuator (3) are withdrawn to the limit position, the internal sensor transmits a signal to the control box (7), the control box (7) controls the first linear actuator (2) and the second linear actuator (3) to stop working and remain self-locking, the control box (7) controls the third linear actuator output shaft (4a) of the third linear actuator to extend, the first linear actuator (2) and the second linear actuator (3) remain self-locking, and the docking guide rail (8) separates from the two side fixed guide rails under the action of the third linear actuator output shaft (4a) of the third linear actuator, without hindering the closing or opening of the aircraft tail door.

8. A method of butt joining the rails of an electric trolley jib crane on an aircraft as defined in claim 6, wherein, The specific process of the control box (7) controlling the docking guide rail (8) to separate from the two side fixed guide rails is as follows: the control box (7) controls the third linear actuator output shaft (4a) of the third linear actuator to be withdrawn, when the third linear actuator output shaft (4a) of the third linear actuator is withdrawn to the limit position, the internal sensor transmits a signal to the control box (7), the control box (7) controls the third linear actuator (4) to stop working and remain self-locking; the control box (7) controls the first linear actuator output shaft (2a) of the first linear actuator and the second linear actuator output shaft (3a) of the second linear actuator to extend at the same speed at the same time, which drives the docking guide rail (8) to move vertically downward, when the docking guide rail (8) is flush with the two side fixed guide rails, the first linear actuator output shaft (2a) of the first linear actuator and the second linear actuator output shaft (3a) of the second linear actuator stop moving and remain self-locking.

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