Aircraft cockpit door electromagnetic lock module with power-off reset and anti-blocking function

Abstract

This invention provides an electromagnetic lock module for an aircraft cockpit door with power-off reset and anti-blocking functions, belonging to the field of aircraft avionics system technology. It includes a base, housing, door locking mechanism, stepper motor assembly, control circuit board, and status detection module. The door locking mechanism includes an anti-blocking hook assembly and a locking pin assembly. The stepper motor assembly is energized only momentarily during action, driving the locking pin to move and achieve locking and unlocking, solving the problems of overheating, high energy consumption, and short lifespan caused by continuous power supply in traditional electromagnetic locks. The module integrates multiple detections, including locking pin position and door position, for real-time status monitoring. A specially designed anti-blocking transmission mechanism allows for separation and automatic reset when the locking pin is jammed, preventing damage. The module has an automatic release function upon power failure, ensuring reliability for emergency evacuation. This invention features a robust structure, high fault tolerance, and meets aviation standard requirements.

Description

Technical Field

[0001] This invention belongs to the field of aircraft avionics system technology, specifically relating to an electromagnetic lock module for an aircraft cockpit door with power failure reset and anti-blocking functions, which is particularly suitable for the cockpit door control system of civil passenger aircraft. Background Technology

[0002] The cockpit door electromagnetic lock module is a critical component for ensuring flight safety and a core barrier preventing unauthorized personnel from entering the aircraft cockpit. During normal flight and takeoff / landing, this module must maintain the cockpit door reliably locked to prevent external interference or unauthorized intrusion, thereby enhancing flight safety and operational reliability. Traditional cockpit door electromagnetic locks generally use solenoids as the drive source. During operation, these electromagnetic locks require continuous energization of the solenoid coil to maintain the locked or unlocked state. This operating mode brings significant drawbacks: First, continuous energization causes the solenoid coil to overheat, accelerating insulation aging and significantly shortening the lifespan and reliability of the electromagnetic lock; second, continuous power consumption increases the aircraft's electrical burden, failing to meet the requirements of modern aviation systems for green energy conservation and efficient power supply. More critically, in the event of a power outage or malfunction, traditional electromagnetic locks rely solely on the spring force to pull back the locking pin to unlock. If the spring fails due to fatigue, jamming, or breakage, unlocking will fail, severely hindering crew evacuation or external rescue in emergencies, posing a significant safety hazard. Therefore, there is an urgent need for a new type of electromagnetic lock module for cockpit doors that can overcome the above-mentioned defects, has high reliability, low power consumption, and can ensure successful unlocking even in the event of a power outage. Summary of the Invention

[0003] The technical problem solved by this invention is to provide an electromagnetic lock module for an aircraft cockpit door with power-off reset and anti-blocking functions. This invention aims to solve the problems of heat generation, short lifespan, and high energy consumption caused by continuous power supply in traditional electromagnetic locks, as well as the risk of failure due to unlocking by relying solely on spring force.

[0004] To achieve the above objectives, the present invention adopts the following technical solution: An electromagnetic lock module for an aircraft cockpit door with power-off reset and anti-blocking functions includes a base, on which a housing is mounted, the housing being connected to the base to form a receiving space. Within the receiving space are a stepper motor assembly, a control circuit board, a door locking mechanism, a lock pin position detection module, and a door position detection module. The door locking mechanism includes an anti-blocking hook assembly and an anti-blocking pin assembly, the anti-blocking pin assembly being used to lock or release the anti-blocking hook assembly. The stepper motor assembly is driven by the door locking mechanism and is used to drive the anti-blocking pin assembly to move between a first position and a second position to lock and release the anti-blocking hook assembly, wherein the stepper motor assembly is energized only during movement between the first and second positions. The control circuit board is electrically connected to the stepper motor assembly and is used to receive control commands and control the movement of the stepper motor assembly. The lock pin position detection module is used to detect the position state of the anti-blocking pin assembly and is electrically connected to the control circuit board. The door position detection module is used to detect the open / closed state of the cockpit door and is electrically connected to the control circuit board. The connector is mounted on the housing and electrically connected to the control circuit board for power and signal transmission with the control unit in the cockpit.

[0005] The stepper motor assembly includes a stepper motor, a reduction mechanism, and a motor position detection module. The output of the stepper motor is connected to the input of the reduction mechanism, and the output of the reduction mechanism is connected to an anti-blocking locking pin assembly. The motor position detection module is used to detect the movement position of the stepper motor and send a motor position status signal to the control circuit board.

[0006] Furthermore, the anti-blocking lock pin assembly of the door locking mechanism includes a lock pin and a lock pin torsion spring, and the anti-blocking lock hook assembly includes a lock hook; when the stepper motor assembly drives the lock pin to move to the first position, the lock pin engages the lock hook to restrict its rotation, thereby locking; when the stepper motor assembly drives the lock pin to move to the second position, the lock pin disengages from the lock hook, allowing it to rotate, thereby unlocking.

[0007] Furthermore, the door locking mechanism also includes an anti-blocking transmission mechanism. The stepper motor assembly is connected to the locking pin through the anti-blocking transmission mechanism. The anti-blocking transmission mechanism consists of two separable transmission mechanisms, including transmission plate I and transmission plate II. Both transmission plate I and transmission plate II are rotatably mounted on a support shaft, which is fixed to the housing. One end of each transmission plate I and transmission plate II is used to mate with the locking pin. The other end of transmission plate I is provided with a stop bar for contacting the other end of transmission plate II. Both transmission plate I and transmission plate II are provided with a return torsion spring. When the stepper motor assembly moves to the right to lock, transmission plate I and transmission plate II move clockwise around the support shaft under the action of the return torsion spring. When a blockage occurs, only transmission plate I is blocked, while transmission plate II can continue to move. When the blockage is released, transmission plate I reaches the locked position under the action of its corresponding return torsion spring. When the motor moves to the left to unlock, transmission plate II, blocked by the stop bar, drives transmission plate I to move counterclockwise to pull open the locking pin and unlock.

[0008] Furthermore, the door position detection module includes a latch detection rod, a torsion spring, a slider, and a latch position detection switch; the torsion spring and the latch detection rod are connected by a shaft, and the connection end between the latch detection rod and the slider is wedge-shaped. When the latch detection rod rotates, the wedge will rotate and squeeze the slider to move forward, thereby triggering the contact of the position detection switch.

[0009] Furthermore, the control circuit board includes a processor module, a power management module, a motor drive module, and a CAN communication module; the processor module receives the control command through the CAN communication module and controls the motor drive module according to the control command to drive the stepper motor assembly; the processor module also receives status signals from the lock pin position detection module and the door position detection module, and reports them through the CAN communication module.

[0010] Furthermore, the base is made of cast steel, the housing is made of stainless steel and aluminum alloy, and the connection between the housing and the base is sealed; the connector is an aviation connector.

[0011] Furthermore, the electromagnetic lock module for the aircraft cockpit door is configured to automatically switch to the unlocked state when the aircraft is powered off, and the lock pin is reset to the second position under the force of the lock pin torsion spring to release the lock hook.

[0012] Advantages of this invention compared to existing technologies: 1. Low power consumption and long lifespan: This solution uses a stepper motor instead of a traditional solenoid, and is powered only during the locking and unlocking actions, resulting in almost no power consumption and heat generation, which greatly extends the module's lifespan and improves reliability; 2. This solution offers high unlocking reliability: Active unlocking is achieved through a bidirectional stepper motor drive combined with a transmission mechanism, fundamentally eliminating the risk of unlocking failure that may result from the traditional structure relying solely on spring force to passively pull back the locking pin. Simultaneously, the system features an automatic release function upon power failure, ensuring reliable unlocking in emergency situations. 3. This solution features anti-blocking and self-resetting functions: A unique anti-blocking transmission mechanism is designed, consisting of two separable parts. When the locking hook and locking pin become stuck, the transmission mechanism on the motor side can continue to operate independently, preventing motor stall and damage. After the blockage is cleared, all components automatically reset under the action of torsion springs, greatly enhancing the system's fault tolerance. 4. This solution features comprehensive status monitoring: It integrates multiple detection modules such as lock pin position, hatch position, and motor position, enabling real-time and comprehensive monitoring of the electromagnetic lock and hatch status, and timely reporting to the cockpit control unit via the bus, thus achieving intelligent management; 5. This solution features a robust and durable structure: the base, shell, and main internal load-bearing components are all made of high-strength stainless steel and other materials, and are sealed to withstand challenges such as vibration, temperature changes, and dust intrusion in the aviation environment. Attached Figure Description

[0013] Figure 1 This is a front structural schematic diagram of the electromagnetic lock module for the aircraft cockpit door of the present invention; Figure 2 This is a schematic diagram of the rear structure of the electromagnetic lock module for the aircraft cockpit door of the present invention; Figure 3 This is a three-dimensional structural diagram of the electromagnetic lock module for the aircraft cockpit door of the present invention. Figure 1 ; Figure 4 This is a three-dimensional structural diagram of the electromagnetic lock module for the aircraft cockpit door of the present invention. Figure 2 ; Figure 5 This is a schematic diagram of the anti-blocking transmission mechanism in this invention; Figure 6 This is a schematic diagram of the electromagnetic lock circuit of the present invention. Detailed Implementation

[0014] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0015] Please see Figure 1-6 The embodiments of the present invention are described in detail below.

[0016] See Figure 1-4 As shown, an electromagnetic lock module for an aircraft cockpit door with power-off reset and anti-blocking functions includes a base 1, a housing 2 on the base 1, and the housing 2 connected to the base 1 to form a receiving space. The receiving space contains a stepper motor assembly 4, a control circuit board 5, a door locking mechanism 6, a lock pin position detection module 7, and a door position detection module 8. The door locking mechanism 6 includes an anti-blocking hook assembly and an anti-blocking lock pin assembly. The anti-blocking lock pin assembly is used to lock or release the anti-blocking hook assembly. The anti-blocking lock pin assembly of the door locking mechanism 6 includes a lock pin 9 and a lock pin torsion spring, and the anti-blocking lock hook assembly includes a lock hook 10. When the stepper motor assembly 4 drives the lock pin 9 to move to the first position, the lock pin 9 engages the lock hook 10 to restrict its rotation, thus locking. When the stepper motor assembly 4 drives the lock pin 9 to move to the second position, the lock pin 9 disengages from the lock hook 10, allowing it to rotate, thus unlocking.

[0017] See Figure 5 As shown, the hatch locking mechanism 6 also includes an anti-blocking transmission mechanism 11. The stepper motor assembly 4 is connected to the locking pin 9 through the anti-blocking transmission mechanism 11. The anti-blocking transmission mechanism 11 consists of two separable transmission mechanisms, including a transmission plate I 19 and a transmission plate II 20. Both transmission plate I 19 and transmission plate II 20 are rotatably mounted on a support shaft 21, which is fixed to the housing 2. One end of each transmission plate I 19 and transmission plate II 20 is used to mate with the locking pin 9, and the other end of transmission plate I 19 is provided with a stop bar 23 for contacting the other end of transmission plate II 20. Both transmission plate I19 and transmission plate II20 are equipped with reset torsion springs 22. When the stepper motor assembly 4 moves to the right to lock, transmission plate I19 and transmission plate II20 move clockwise around the support shaft 21 under the action of the reset torsion springs 22. When a blockage occurs, only transmission plate I19 is blocked, while transmission plate II20 can continue to move. When the blockage is cleared, transmission plate I19 reaches the locked position under the action of its corresponding reset torsion spring 22. When the motor moves to the left to unlock, transmission plate II20, under the obstruction of the stop lever 23, drives transmission plate I19 to move counterclockwise to pull open the locking pin 9 and unlock.

[0018] The locking pin position detection module 7 is used to detect the position status of the anti-blocking locking pin assembly and is electrically connected to the control circuit board 5. The stepper motor assembly 4 is driven by the door locking mechanism 6 and is used to drive the anti-blocking locking pin assembly to move between the first position and the second position to lock and release the anti-blocking locking hook assembly. The stepper motor assembly 4 is only energized during the movement between the first position and the second position.

[0019] The stepper motor assembly 4 includes a stepper motor 16, a reduction mechanism 17, and a motor position detection module 18. The output of the stepper motor 16 is connected to the input of the reduction mechanism 17, and the output of the reduction mechanism 17 is connected to an anti-blocking locking pin assembly. The motor position detection module 18 is used to detect the movement position of the stepper motor 16 and send a motor position status signal to the control circuit board 5. The control circuit board 5 is electrically connected to the stepper motor assembly 4 and is used to receive control commands and control the operation of the stepper motor assembly 4. Figure 6 As shown, the control circuit board 5 includes a processor module, a power management module, a motor drive module, and a CAN communication module. The power management module is responsible for converting the aircraft's input power into the secondary power required by each module and providing protection. The processor module is the control core of the entire electromagnetic lock. The processor module receives the control commands through the CAN communication module and controls the motor drive module according to the control commands to drive the stepper motor assembly 4. The processor module also receives status signals from the lock pin position detection module 7 and the door position detection module 8 and reports them through the CAN communication module. The door position detection module 8 is used to detect the opening and closing status of the cockpit door and is electrically connected to the control circuit board 5. The door position detection module 8 includes a latch detection rod 13, a torsion spring 14, a slider 15, and a latch position detection switch 12. The torsion spring 14 is connected to the latch detection rod 13 through a shaft. The connection end between the latch detection rod 13 and the slider 15 is wedge-shaped. When the latch detection rod 13 rotates, the wedge will rotate and squeeze the slider 15 to move forward, thereby triggering the contact of the position detection switch 12. When the cockpit door's latch enters the anti-blocking hook assembly, it rotates the latch detection rod 13, which in turn pushes the slider 15 to move and triggers the latch position detection switch 12 to detect whether the cockpit door is in the closed state. Connector 3 is mounted on housing 2 and electrically connected to control circuit board 5 for power and signal transmission with the control unit inside the cockpit.

[0020] Base 1, serving as the load-bearing foundation of the entire module, is made of high-strength cast steel (such as ZG310-570) and precision machined. Housing 2 uses 304 stainless steel as its frame, covered with an aluminum alloy shell, balancing structural strength and lightweight requirements. The connections between housing 2 and base 1 are sealed to minimize the ingress of dust and moisture. Connector 3 uses a high-reliability D38999 series circular aviation connector, mounted on the head of housing 2 with four M5 countersunk screws. It connects to the control unit in the cockpit via a shielded cable, enabling power supply and CAN bus communication.

[0021] The electromagnetic lock module for the aircraft cockpit door is configured to automatically switch to the unlocked state when the aircraft loses power. The locking pin 9 is reset to the second position under the force of the locking pin torsion spring to release the locking hook 10.

[0022] The working process and principle of this invention are as follows: Locking Process: When the processor module receives the "lock" command from the cockpit control unit via the CAN bus, it immediately controls the motor drive module to supply power to the stepper motor assembly, driving it to rotate forward. The stepper motor, after torque amplification via a reduction mechanism, pushes the anti-blocking transmission mechanism to extend. The transmission mechanism overcomes the spring force of the lock pin torsion spring, pushing the lock pin from the unlocked position to the locked position, ultimately engaging in the lock hook's slot, preventing the lock hook from rotating. At this point, the cockpit door latch enters the lock hook, achieving mechanical locking of the cockpit door. The motor stops working, and the position is maintained. During this process, the motor is only energized for a few seconds when receiving the command, and then de-energized. Door Closing Detection Process: Simultaneously with the latch entering the lock hook to complete locking, the latch presses against the latch detection rod of the door position detection module. The rotation of the detection rod pushes a slider forward; once the slider is in position, it triggers a microswitch at the end of its travel. The change in the state of the microswitch (e.g., from open to closed) is captured by the processor module, which determines that "the hatch is closed" and reports this status information to the control unit in real time via the CAN bus.

[0023] Unlocking process: When the processor module receives the "unlock" command, it controls the motor drive module to supply reverse power to the stepper motor assembly, driving it to rotate in the opposite direction. The stepper motor drives the anti-blocking transmission mechanism to retract, and the locking pin, with the assistance of its own torsion spring, disengages from the locking hook slot and returns to the unlocked position. The locking hook regains its free rotation capability, at which point personnel can push and pull the hatch to open it. The motor is also de-energized after the operation is completed.

[0024] Door opening detection process: When the hatch is pushed open, the latch disengages from the latch hook, releasing pressure on the latch detection rod. The detection rod resets under the action of its own torsion spring, and the linked slider also moves to the left and resets under the force of the microswitch, restoring the microswitch to its original state (e.g., from closed to open). The processor detects this state change, determines that "the hatch has been opened," and reports it. Anti-blocking mechanism principle: The anti-blocking transmission mechanism of this invention consists of two separable transmission components, such as a clutch structure with a ramp or spring loading. In rare cases, if the latch hook and the locking pin become stuck and cannot move, a "blockage" occurs. At this time, when the first transmission mechanism connected to the stepper motor executes the motor's forward command, the increased resistance compresses the internal spring, causing it to separate from the stuck second transmission mechanism (connected to the locking pin), and it continues to move forward. This avoids damage to the motor due to stalling. Once the foreign object or jamming cause is removed—for example, if the door is slightly pushed to reduce the force on the locking hook—the jammed locking pin and the second transmission mechanism will instantly spring back to their normal position under the strong force of their own torsion springs, and re-engage with the already positioned first transmission mechanism. The entire system will then function normally without manual intervention. Automatic release and mechanical backup in case of power failure: When the aircraft experiences an emergency power failure, the system loses power, and the holding torque of the stepper motor assembly disappears. At this time, the locking pin, which is in the locked state, will overcome the frictional force of the mechanism under the strong elastic force of its stored torsion spring, automatically springing back from the first position (locked position) to the second position (unlocked position). The locking hook will release, and the cabin door can be easily pushed open, ensuring an unobstructed emergency evacuation route.

[0025] The key feature of this invention is that the cockpit door electromagnetic lock module ensures the cockpit door remains locked during normal flight and takeoff / landing, preventing external interference or unauthorized personnel from entering the cockpit. The module boasts high reliability and durability, capable of withstanding various challenges in the aviation environment. It also features an automatic release function in the event of a power outage, ensuring rapid evacuation of the crew in abnormal situations. Furthermore, the module includes a fault detection and alarm system that monitors the locking status in real time and promptly reports potential problems. The application of this cockpit door electromagnetic lock module not only enhances safety but also improves convenience and reliability.

[0026] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered in all respects as exemplary and non-limiting, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the present invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0027] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. An electromagnetic lock module for an aircraft cockpit door with power-off reset and anti-blocking functions, characterized in that: The system includes a base (1), on which a housing (2) is provided. The housing (2) is connected to the base (1) and forms a receiving space. A stepper motor assembly (4), a control circuit board (5), a hatch locking mechanism (6), a lock pin position detection module (7), and a hatch position detection module (8) are provided in the receiving space. The hatch locking mechanism (6) includes an anti-blocking hook assembly and an anti-blocking lock pin assembly. The anti-blocking lock pin assembly is used to lock or release the anti-blocking hook assembly. The stepper motor assembly (4) is drivenly connected to the hatch locking mechanism (6) and is used to drive the anti-blocking lock pin assembly in a first position and a second position. The device moves between two positions to lock and release the anti-blocking lock hook assembly, wherein the stepper motor assembly (4) is energized only during the movement between the first and second positions; the control circuit board (5) is electrically connected to the stepper motor assembly (4) and is used to receive control commands and control the action of the stepper motor assembly (4); the lock pin position detection module (7) is used to detect the position state of the anti-blocking lock pin assembly and is electrically connected to the control circuit board (5); the hatch position detection module (8) is used to detect the opening and closing state of the cockpit door and is electrically connected to the control circuit board (5). The connector (3) is installed on the housing (2) and electrically connected to the control circuit board (5), and is used to transmit power and signals to the control unit in the cockpit.

2. The aircraft cockpit door electromagnetic lock module with power failure reset and anti-blocking functions as described in claim 1, characterized in that: The stepper motor assembly (4) includes a stepper motor (16), a reduction mechanism (17), and a motor position detection module (18). The output of the stepper motor (16) is connected to the input of the reduction mechanism (17), and the output of the reduction mechanism (17) is connected to the anti-blocking locking pin assembly. The motor position detection module (18) is used to detect the moving position of the stepper motor (16) and send a motor position status signal to the control circuit board (5).

3. The aircraft cockpit door electromagnetic lock module with power failure reset and anti-blocking functions as described in claim 1, characterized in that: The door locking mechanism (6) includes a locking pin assembly (9) and a locking pin torsion spring, and an anti-blocking hook assembly (10). When the stepper motor assembly (4) drives the locking pin (9) to move to the first position, the locking pin (9) locks the hook (10) to restrict its rotation, thereby locking. When the stepper motor assembly (4) drives the locking pin (9) to move to the second position, the locking pin (9) disengages from the hook (10) to allow it to rotate, thereby unlocking.

4. The aircraft cockpit door electromagnetic lock module with power failure reset and anti-blocking functions according to claim 3, characterized in that: The door locking mechanism (6) also includes an anti-blocking transmission mechanism (11). The stepper motor assembly (4) is connected to the locking pin (9) through the anti-blocking transmission mechanism (11). The anti-blocking transmission mechanism (11) consists of two separable transmission mechanisms, including a transmission plate I (19) and a transmission plate II (20). Both the transmission plate I (19) and the transmission plate II (20) can be rotatably mounted on a support shaft (21). The support shaft (21) is fixed on the housing (2). One end of both the transmission plate I (19) and the transmission plate II (20) is used to fit with the locking pin (9). The other end of the transmission plate I (19) is provided with a stop bar (23) and is used to connect with the other end of the transmission plate II (20). Both transmission plate I (19) and transmission plate II (20) are provided with reset torsion springs (22). When the stepper motor assembly (4) moves to the right to lock, transmission plate I (19) and transmission plate II (20) move clockwise around the support shaft (21) under the action of the reset torsion springs (22). When a blockage occurs, only transmission plate I (19) is blocked, while transmission plate II (20) can continue to move. When the blockage is released, transmission plate I (19) reaches the locked position under the action of its corresponding reset torsion springs (22). When the motor moves to the left to unlock, transmission plate II (20) drives transmission plate I (19) to move counterclockwise under the obstruction of the stop lever (23) to pull open the locking pin (9) and unlock.

5. The aircraft cockpit door electromagnetic lock module with power failure reset and anti-blocking functions according to claim 1, characterized in that: The door position detection module (8) includes a latch detection rod (13), a torsion spring (14), a slider (15), and a latch position detection switch (12). The torsion spring (14) is connected to the latch detection rod (13) via a shaft. The connection end between the latch detection rod (13) and the slider (15) is wedge-shaped. When the latch detection rod (13) rotates, the wedge will rotate and squeeze the slider (15) to move forward, thereby triggering the contact of the position detection switch (12).

6. The aircraft cockpit door electromagnetic lock module with power failure reset and anti-blocking functions according to claim 1, characterized in that: The control circuit board (5) includes a processor module, a power management module, a motor drive module and a CAN communication module; the processor module receives the control command through the CAN communication module and controls the motor drive module according to the control command to drive the stepper motor assembly (4); the processor module also receives status signals from the lock pin position detection module (7) and the door position detection module (8) and reports them through the CAN communication module.

7. The aircraft cockpit door electromagnetic lock module with power failure reset and anti-blocking functions according to claim 1, characterized in that: The base (1) is made of cast steel, the housing (2) is made of stainless steel and aluminum alloy, and the connection between the housing (2) and the base (1) is sealed; the connector (3) is an aviation connector.

8. The aircraft cockpit door electromagnetic lock module with power failure reset and anti-blocking functions according to claim 1, characterized in that: The electromagnetic lock module for the aircraft cockpit door is configured to automatically switch to the unlocked state when the aircraft is powered off, and the lock pin (9) is reset to the second position under the force of the lock pin torsion spring to release the lock hook (10).

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