Double hook locking device

Abstract

The double-hook locking device disclosed by the application relates to the field of aircraft cabin door lock mechanism design. The device mainly comprises two symmetrical lock hooks arranged above the split cabin door, lock hook tension springs connected with the lock hook stop rods of the parallel inner fixed supports of the two lock hook supports, a double-fork support arm linkage mechanism connected with the lock hooks and arranged on the hinge seats corresponding to the lock hook tension springs, a linkage lock hook fixed on the lock spring seat and arranged on the connecting rod of the stop rocker arm connected with the rotating pair of the linkage mechanism, a stop rocker arm tension spring guided by a rigid body, a piston rod actuating surface built in the actuating cylinder 5 connected with the tension spring rocker arm connecting rod on the double-fork support arm, and the double-hook locking device in the open / locked state of the linkage lock hook. The application realizes quick unlocking by using gas / liquid pressure, the split cabin door lock mechanism has high safety and reliability in corresponding locking, can simplify the aircraft control logic, and can realize non-synchronous triggering of locking and unlocking. The reliability, safety and maintainability of the locking device are improved.

Description

Technical Field

[0001] This invention relates to the field of aircraft cabin door locking mechanism design, and specifically to a double-hook locking device suitable for aircraft "double-opening cabin doors". Background Technology

[0002] The aircraft door locking mechanism is a crucial component that performs both locking and load-bearing functions. During high-speed flight, the various doors on an aircraft bear significant aerodynamic loads. To maintain a good aerodynamic shape and prevent excessive deformation of the doors under these loads, door locks are typically installed on the doors to reliably lock them to the fuselage. For "double-leaf" doors, two upper locks are usually required to lock both doors. These two upper locks not only increase the aircraft's weight but also complicate the design of their installation locations. Furthermore, during door retraction, the door retraction actuators often cannot guarantee that both doors reach the retracted position simultaneously, resulting in different locking sequences for the two upper locks. Therefore, the locking control logic of the upper locks also requires sophisticated control. Summary of the Invention

[0003] The purpose of this invention is to address the shortcomings of traditional locking methods for "double-leaf hatches" and the problem of asynchronous closing of the two hatches. It proposes a double-hook locking device that provides high locking security and reliability for double-leaf hatches, simplifies aircraft control logic, and enables asynchronous locking and unlocking. This device can simultaneously lock both hatches.

[0004] To solve the above problems, the present invention provides the following technical solution: a double-hook locking device, comprising: a hook 1 mounted above a split hatch, with two symmetrical hook supports hinged together, and a hook spring 2 parallel to the hook supports and linked to the hook 1 stop rod via an inner fixed support, characterized in that: on a hinge seat parallel to the hook spring 2 inward, a double-fork support arm linkage mechanism is provided to connect the hook 1; on the connecting rod of the stop rocker arm 3 connected to the rotating joint of the linkage mechanism, a stop rocker arm spring 4 is provided to link the hook 1 and is rigidly guided on the lock spring seat; the stop rocker arm spring 4 is connected to the piston rod actuating surface 9 inside the actuating cylinder 5 via the spring rocker arm linkage on the double-fork support arm, forming a double-hook locking device in the open / locked state of the hook 1.

[0005] Compared with the prior art, the present invention has the following advantages:

[0006] This invention integrates two independent locking mechanisms. During locking, it enables asynchronous locking of the left and right cabin doors. During unlocking, a single actuator simultaneously drives both locking mechanisms, allowing for synchronous unlocking of the left and right cabin doors. Structurally, integrating the two locking mechanisms into one unit and driving them through the same unlocking actuator simplifies the locking device structure, reduces installation space and weight, and simplifies aircraft control logic. Utilizing pneumatic / hydraulic pressure for rapid unlocking improves the reliability, safety, and maintainability of the locking device. This invention provides high locking and unlocking safety for the cabin door locking mechanism, simplifies aircraft control logic, and enables asynchronous triggering of locking and unlocking. Attached Figure Description

[0007] Figure 1 This is a schematic diagram of the static structure of the double-hook locking device of the present invention;

[0008] Figure 2 yes Figure 1 A schematic diagram of the dynamic unlocking principle;

[0009] Figure 3 yes Figure 1 Schematic diagram of the actuator;

[0010] Figure 4 yes Figure 1 Diagram of the locking hook;

[0011] Figure 5 This is a schematic diagram of the hatch product.

[0012] In the diagram: 1. Locking hook, 2. Locking hook tension spring, 3. Anti-rocker arm, 4. Anti-rocker arm tension spring, 5. Actuating cylinder, 6. Piston rod, 7. Locking nozzle, 8. Piston rod, 9. Piston rod actuating surface, 10. Hydraulic unlocking nozzle, 11. Emergency unlocking nozzle, 12. Cylinder, 13. Downward bearing locking hook, 14. Locking contact surface, 15. Stopping surface, 16. Hatch door, 17. Locking ring, 18. Hatch door movement trajectory.

[0013] The specific embodiments provided by the present invention will be described in detail below with reference to the accompanying drawings. Detailed Implementation

[0014] See Figure 1 , Figure 2In a preferred embodiment described below, a double-hook locking device includes: a hook 1 hinged above a split hatch, with two symmetrical hook supports connected by hinges; and a hook spring 2 parallel to the hook supports and linked to the hook 1 stop rod by an inner fixed support. The device is characterized in that: a double-fork arm linkage mechanism connecting the hook 1 is provided on a hinge seat parallel to the hook spring 2; a stop rocker arm spring 4, rigidly guided by a locking hook 1 and fixed to a spring seat, is provided on the connecting rod of a stop rocker arm 3 connected to the rotating joint of the linkage mechanism; the stop rocker arm spring 4 is connected to the piston rod actuating surface 9 inside the actuating cylinder 5 via the spring rocker arm linkage on the double-fork arm, forming a double-hook locking device in the open / locked state of the hook 1.

[0015] The aforementioned double-hook locking device is connected to the door frame structure via mounting bolts and is used to bear the load of the split hatch. The actuating surface 9 on the piston rod 6 is connected to the symmetrical double-fork support arm linkage mechanism, which in turn links the symmetrical lock hook tension spring 2 to drive the symmetrical double-hook lock hook 1 to swing and rotate, thereby realizing the symmetrical double-hook lock hook 1 rotating to unlock and lock under the load of the hatch.

[0016] Furthermore, in the open / locked state of the locking device, the symmetrical anti-rocker arm tension spring 4 restricts the rotational freedom of the symmetrical locking hook 1 under the door load through the symmetrical anti-rocker arm 3.

[0017] Furthermore, in the unlocked / locked state of the locking device, the double fork arm linkage mechanism applies a pushing and pulling force to the symmetrical anti-rocker arm tension spring 4 and the symmetrical anti-rocker arm 3 through the piston rod actuating surface 9, thereby driving the symmetrical double hook lock 1 to rotate. This ensures that the symmetrical lock hook 1, symmetrical lock hook tension spring 2, symmetrical anti-rocker arm 3, and anti-rocker arm tension spring 4 remain in the unlocked and locked states after the aircraft hydraulic system is depressurized, preventing the locking device from accidentally unlocking or locking due to vibrations, impacts, or other operating conditions on the aircraft.

[0018] The double fork arm linkage mechanism forms an M-shaped dynamic linkage symmetrical double hook lock 1 by connecting the symmetrical stop rocker arm 3 to the piston rod actuating surface 9, thus constituting a closed-chain planar linkage mechanism with relative motion.

[0019] Furthermore, in both the locked and unlocked states, the locking ring 17 installed on the hatch 16, driven by the hatch movement trajectory 18, impacts and triggers the locking trigger surface 14 on the cross lock bar of the symmetrical locking hook 1, causing the symmetrical locking hook 1 to rotate. When the symmetrical locking hook rotates to the locked position, the symmetrical anti-rocker arm 3, under the action of the symmetrical anti-rocker arm tension spring 4, contacts the stop surface 15 on the cross lock bar of the symmetrical locking hook. At this time, the load applied by the locking ring 17 to the downward bearing surface 13 of the symmetrical locking hook cannot cause the locking hook to rotate, and the hatch is locked in the locked position by the double hooks. Since a set of symmetrical double hook locking mechanisms is arranged on each side of the double hook locking mechanism, and the two sets of symmetrical double hook locking mechanisms are symmetrical and independent about the actuator 5, asynchronous locking of the left and right hatches can be achieved during the locking process of the "double-opening" left and right hatches. When the aircraft lands, pressure is supplied to the hydraulic unlocking nozzle 10 of the actuator cylinder, and the piston rod actuating surface 9 simultaneously pushes the two symmetrical anti-rocker arms to separate from the symmetrical locking hook stop surfaces. The locking effect of the symmetrical locking hook 1 on the upper locking ring 17 disappears, and the cabin door opens under the action of the retraction actuator cylinder. When the aircraft hydraulic system malfunctions, pressure is supplied to the emergency unlocking nozzle 11 of the actuator cylinder, which can also achieve locking and unlocking.

[0020] See Figure 3 , Figure 4 The actuator assembly includes: a piston rod 8 that reciprocates within the cylinder 12 of the actuator 5; a locking nozzle 7 connecting to the cylinder 12; a hydraulic unlocking nozzle 10 located on the right side of the piston rod's actuating surface 9; and an emergency unlocking nozzle 11. (See reference...) Figure 4 The locking hook 1 has a cross locking bar, which is connected to the locking hook spring 2 and the support arm of the double fork support arm linkage mechanism through a stop bar 15 that is linked to the upper locking trigger rod 14, and carries the locking hook 13 and the upper locking nozzle 7.

[0021] The double fork arm linkage mechanism has two opposing symmetrical double fork arms connected by piston rods 6. The piston rod actuating surface 9 on the rod body drives the inner cylinder 12 of the actuator cylinder 5 to reciprocate, overcoming the elastic force of the stop rocker arm tension spring 4, and driving the tension spring arm to move up and down.

[0022] The embodiments of the present invention have been described in detail above. Without creative effort, other technical solutions can be obtained from the above embodiments, and equivalent changes made within the scope of protection of the present invention should also fall within the scope of protection of the present invention.

Claims

1. A double-hook locking device, comprising: The lock hook spring (2) of the lock hook (1) is a lock hook spring that is set on the inner side fixed support of the two lock hook supports parallel to the two lock hook supports and the lock hook (1) stop rod. The lock hook spring (2) is characterized in that: on the hinge seat parallel to the lock hook spring (2) inward, there is a double fork arm linkage mechanism that connects the lock hook (1). On the linkage of the stop rocker arm (3) connected to the rotating part of the linkage mechanism, there is a linkage lock hook (1) and it is fixed on the lock spring seat. The stop rocker arm spring (4) guided by the rigid body is connected to the piston rod actuating surface (9) inside the actuating cylinder (5) through the spring rocker arm linkage on the double fork arm to form a double hook locking device in the open / locked state of the linkage lock hook (1). In the unlocked / locked state of the locking device, the double fork arm linkage mechanism pushes and pulls the symmetrical anti rocker arm tension spring (4) and the symmetrical anti rocker arm (3) through the piston rod actuating surface (9), driving the symmetrical double hook lock (1) to rotate, so that the symmetrical lock hook (1), the symmetrical lock hook tension spring (2), the symmetrical anti rocker arm (3) and the anti rocker arm tension spring (4) can remain in the unlocked and locked state after the pressure of the aircraft hydraulic system is cut off; The double fork arm linkage mechanism forms an M-shaped dynamic linkage symmetrical double hook lock (1) by connecting the actuating surface (9) of the piston rod (6) with the symmetrical stop rocker arm (3), thus constituting a closed-chain planar linkage mechanism with relative motion. The double hook lock is arranged with a symmetrical double hook locking mechanism on each side. The two symmetrical double hook locking mechanisms are symmetrical about the actuator (5) and independent of each other. During the locking process of the left and right hatches, the left and right hatches are locked asynchronously.

2. The double-hook locking device as described in claim 1, characterized in that: The aforementioned double-hook locking device is connected to the door frame structure via mounting bolts and is used to bear the load of the split hatch.

3. The double-hook locking device as described in claim 1, characterized in that: The actuating surface (9) on the piston rod (6) is connected to the symmetrical double fork support arm linkage mechanism, which is linked to the symmetrical lock hook tension spring (2) to drive the symmetrical double hook lock hook (1) to swing and rotate, so as to realize the symmetrical double hook lock hook (1) to rotate and lock under the door load.

4. The double-hook locking device as described in claim 1, characterized in that: In the open / locked state of the locking device, the symmetrical stop rocker arm tension spring (4) restricts the rotational freedom of the symmetrical lock hook (1) under the door load through the symmetrical stop rocker arm (3).

5. The double-hook locking device as described in claim 1, characterized in that: In the locked and unlocked states of the double hooks, the locking ring (17) installed on the hatch (16) strikes the trigger surface (14) on the cross lock bar of the symmetrical locking hook (1) under the action of the hatch movement trajectory (18), causing the symmetrical locking hook (1) to rotate; when the symmetrical locking hook rotates to the locked position, the symmetrical anti-rocker arm (3) contacts the stop surface (15) on the cross lock bar of the symmetrical locking hook under the action of the symmetrical anti-rocker arm tension spring (4). At this time, the load applied by the locking ring (17) to the symmetrical locking hook bearing the downward locking hook (13) cannot cause the locking hook to rotate, and the hatch is locked in the locked position by the double hooks.

6. The double-hook locking device as described in claim 1, characterized in that: When the aircraft lands, pressure is supplied to the hydraulic unlocking nozzle (10) of the actuator cylinder, and the piston rod actuating surface (9) simultaneously pushes the two symmetrical stop rocker arms to separate from the symmetrical lock hook stop surface. The locking effect of the symmetrical lock hook (1) on the upper locking ring (17) disappears, and the cabin door opens under the action of the retraction actuator cylinder. When the aircraft hydraulic system malfunctions, pressure is supplied to the emergency unlocking nozzle (11) of the actuator cylinder to achieve locking and unlocking.

7. The double-hook locking device as described in claim 1, characterized in that: The piston rod (6) of the two symmetrical double fork arm connecting rod machine is connected to the piston rod (9) on the piston rod body, which is connected to the piston rod (5) and the inner cylinder (12) of the actuator cylinder (5) to reciprocate, overcoming the elastic force of the stop rocker arm tension spring (4) and driving the tension spring arm to move up and down.

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