Emergency lock post disengaging device and control method thereof

Abstract

An emergency lock post disengaging device and a control method thereof, the emergency lock post disengaging device comprising: a lock post support, the lock post support being in a U shape and comprising a pair of vertical legs in a vertical direction and a horizontal leg in a horizontal direction; a device housing, the device housing being fixed to the vertical leg of the lock post support by a mounting leg and having a moving space formed inside; and a lock post, the lock post being fitted between the pair of vertical legs of the lock post support and abutting against a moving block in the device housing via a connecting block, when the moving block moves to a position completely separated from the connecting block under the action of an external force, the connecting block moves into the moving space under the action of axial pressure and is separated from the lock post, and the lock post is disengaged from between the pair of vertical legs. The emergency lock post disengaging device and the control method thereof can ensure normal lowering of a landing gear when mechanical jamming occurs in an uplock of the landing gear.

Description

Technical Field

[0001] This invention relates to an emergency locking pin release device and its control method, and more specifically, to an emergency locking pin release device and its control method capable of enabling emergency deployment of aircraft landing gear. Background Technology

[0002] The landing gear system is an important component of an aircraft that provides both load-bearing and control functions, playing a crucial role in the safe takeoff and landing of the aircraft.

[0003] The landing gear of an aircraft is an essential support system for takeoff, landing, taxiing, ground movement and parking. It is an important component of the aircraft, mainly used to support the aircraft during takeoff, landing or ground taxiing and for ground movement during this process.

[0004] Specifically, the landing gear plays a supporting, cushioning, and ground steering role during aircraft landing. The landing gear assembly typically has two operating states: retracted and extended. When the landing gear assembly is in the retracted state, the upper landing gear lock secures the landing gear in the retracted position, and the upper door lock secures the door in the closed position. When the landing gear assembly is in the extended state, both the upper landing gear lock and the upper door lock hooks are open, and the landing gear is extended after the door is opened.

[0005] Typically, the "hooks" of the landing gear upper lock and the cabin door upper lock engage with the "locking pins" on the landing gear and cabin door structures to achieve upper locking of the landing gear and cabin doors. If the landing gear fails to deploy due to some malfunction, it will have a significant negative impact on the safety of the aircraft.

[0006] In the past, the landing gear upper lock of civil aircraft usually adopted hydraulic unlocking, electronic unlocking, mechanical cable unlocking and other unlocking methods, and they were usually redundant backups of each other. For example, the normal landing gear lowering used hydraulic unlocking, and the backup lowering used electronic unlocking or mechanical cable unlocking, and vice versa.

[0007] However, the aforementioned unlocking methods all rely on mechanical transmission to open the upper lock's hook. When mechanical obstruction occurs, such as when the upper lock hook is jammed against the locking pin, or when the upper lock's unlocking mechanism is blocked, none of the above unlocking methods—whether hydraulic, electronic, or cable-operated—can open the upper lock's hook to lower the landing gear. Therefore, these unlocking methods suffer from a "single point of failure" due to mechanical obstruction, potentially leading to a dangerous failure event where the landing gear cannot be lowered.

[0008] Therefore, it is desirable to provide an emergency locking pin release device and its control method, which can ensure the normal lowering of the landing gear when the upper locking of the landing gear is mechanically jammed. Summary of the Invention

[0009] This invention is made to solve the above-mentioned technical problems, and its purpose is to provide an emergency locking pin release device and its control method, which can realize the emergency lowering of the landing gear or the emergency opening of the cabin door when the upper lock of the landing gear or the cabin door is mechanically jammed.

[0010] To achieve the objective of this invention, an emergency locking pin release device is provided, capable of releasing a locking pin engaged with a cabin door or landing gear upper lock. The device comprises: a locking pin bracket, the locking pin bracket being U-shaped and including a pair of vertical legs in the vertical direction and a horizontal leg in the horizontal direction; a device housing, the device housing being fixed to the vertical legs of the locking pin bracket by mounting feet and having an internal movable space; and a locking pin, the locking pin being fitted between the pair of vertical legs of the locking pin bracket and abutting against a movable top block inside the device housing via a connecting block. When the movable top block moves to a position completely separated from the connecting block under external force, the connecting block automatically moves into the movable space under axial pressure and separates from the locking pin, thus releasing the locking pin from between the pair of vertical legs.

[0011] According to the above-described configuration, the emergency locking pin release device of the present invention can separate the locking pin from the locking pin bracket connected to the landing gear / landing gear door, and at the same time separate the upper lock hook that is engaged with the locking pin from the landing gear / landing gear door. It can realize the emergency release of the locking pin in the event of mechanical jamming of the upper lock, thereby ensuring the normal opening of the door and the normal lowering of the landing gear.

[0012] Preferably, it also includes a mooring device, one end of which is connected to the lock post bracket and the other end of which is connected to the lock post.

[0013] As described above, by providing a tethering device, the locking pin can be held in place when it is disengaged, preventing it from falling off the aircraft.

[0014] Preferably, an electromagnet is provided in the aforementioned active space, the aforementioned movable top block is made of a magnetizable metal material, and the aforementioned connecting block is made of a non-magnetizable metal material.

[0015] Preferably, the electromagnet abuts against the movable top block through the elastic member, and when the electromagnet is energized, the movable top block is attracted to move towards the elastic member by the electromagnetic effect.

[0016] Based on the configuration described above, the movement of the movable top block can be attracted by the electromagnetic effect generated when the electromagnet is energized, thereby achieving emergency release of the locking pin.

[0017] Preferably, a lubrication port communicating with the active space is provided on the device housing, through which lubricating oil is injected from the outside of the device housing into the active space.

[0018] As described above, by injecting lubricating oil from the outside of the device housing into the active space through the lubrication port, the emergency locking pin disengagement device can operate more smoothly.

[0019] Preferably, the connecting block is in the shape of a stepped frustum, with the bottom surface of the frustum abutting against the movable top block, and the other end face opposite to the bottom surface being embedded into the locking post through the locking post bracket.

[0020] Preferably, the angle of the frustum of the connecting block is designed such that the axial component of the force on the connecting block is greater than the maximum static friction force at the contact surface that contacts the locking column bracket.

[0021] As described above, after the electromagnet is energized and the movable top block moves to a position where it is completely disengaged from the connecting block, the connecting block will automatically slide towards the movable space side of the device housing under axial pressure, so as to realize the disengagement of the locking pin. The structure is simple and the operation is convenient.

[0022] Preferably, the housing of the device is symmetrically arranged on a pair of vertical legs of the locking column bracket, or is arranged on only one of the pair of vertical legs of the locking column bracket.

[0023] According to the configuration described above, by symmetrically arranging the device housing and its internal components on a pair of vertical legs of the locking column bracket, the stability of the detachment device can be guaranteed through redundant design; by arranging them on only one vertical leg, the structure can be simplified and production and manufacturing costs can be saved.

[0024] In response to the aforementioned emergency locking pin disengagement device, this invention also provides an emergency locking pin disengagement control method, which enables the locking pin to disengage when both normal and backup unlocking fail. After activating the normal lowering signal and the backup lowering signal, and after a confirmation period, the method uses signals from the landing gear door status calculation module to determine whether the landing gear door is fully open. If the determination is "no", the method identifies the closed door and activates the emergency disengagement device for the door locking pin. If the method determines that the landing gear door is fully open, and after a confirmation period, the method uses signals from the landing gear status calculation module to determine whether the landing gear is fully lowered. If the determination is "no", the method identifies the not-lowered landing gear and activates the emergency disengagement device for the landing gear locking pin, until the method determines that the landing gear is fully lowered.

[0025] Preferably, the opening / closing status of the landing gear door is identified by a landing gear door opening / closing indicator sensor, and the signal is sent to the landing gear door status calculation module; the retraction / extension status of the landing gear is identified by a landing gear retraction / extension indicator sensor, and the signal is sent to the landing gear status calculation module.

[0026] As described above, the aircraft can be deployed in an emergency or opened in an emergency when the upper lock of the landing gear or the cabin door is mechanically jammed, thereby ensuring the safe landing of the aircraft. Attached Figure Description

[0027] In view of the above objectives, the technical features of the present invention are clearly described in the following technical solutions, and its advantages are apparent from the following detailed description with reference to the accompanying drawings, which illustrate preferred embodiments of the invention by way of example, without limiting the scope of the inventive concept.

[0028] Figure 1A This is a plan view of the emergency locking pin release device of the present invention viewed from the front. Figure 1B This is a plan view taken from the side.

[0029] Figure 2A This is a partial cross-sectional view of the emergency locking pin release device of the present invention, viewed from the front. Figure 2B yes Figure 1A The sectional view obtained by cutting from section AA.

[0030] Figure 3A and Figure 3B These are schematic diagrams illustrating the working principle of the emergency locking pin release device of the present invention during the locking pin release process.

[0031] Figure 4 This is a schematic diagram of the state of the emergency locking pin release device of the present invention after the locking pin is released.

[0032] Figure 5 This is a control system architecture diagram of the emergency locking pin release device of the present invention.

[0033] Figure 6 This is a control flowchart of the control method for the emergency locking pin release device of the present invention.

[0034] Symbol Explanation

[0035] 1. Emergency locking pin release device;

[0036] 11. Locking column bracket;

[0037] 12. Device housing;

[0038] 12a Active top block;

[0039] 12b Elastic element;

[0040] 12c electromagnet;

[0041] 12d connection card block;

[0042] 12e Lubrication port;

[0043] 13 Locking pins;

[0044] 14. Attached items. Detailed Implementation

[0045] Embodiments of the invention will now be described in detail, examples of which are illustrated in the accompanying drawings. Although the invention has been described in conjunction with exemplary embodiments, it should be understood that this specification is not intended to limit the invention to the exemplary embodiments described below. Rather, the invention is intended to cover not only the exemplary embodiments, but also various alternatives, modifications, equivalents, and other embodiments that may be included within the spirit and scope of the invention as defined by the appended claims.

[0046] The following is for reference Figure 1A and Figure 1B The overall structure of the emergency locking pin release device 1 of the present invention will be described.

[0047] like Figure 1A As shown, the emergency locking pin release device 1 of the present invention mainly includes a locking pin bracket 11, a pair of device housings 12, a locking pin 13, and a tethering member 14.

[0048] The aforementioned locking post bracket 11 is approximately U-shaped and includes a pair of vertical legs along the vertical direction and a horizontal leg along the horizontal direction. It is mainly used for mounting the device housing 12 and the locking post 13, and the base of the locking post bracket 11, i.e. the horizontal leg, is fixedly connected to the hatch or landing gear.

[0049] The aforementioned pair of device housings 12 are approximately π-shaped, each having mounting feet extending to both sides, and are individually mounted on a pair of vertical feet of the aforementioned lock post bracket 11.

[0050] The aforementioned locking pin 13 is cylindrical in shape and is engaged as a whole between a pair of vertical legs of the U-shaped locking pin bracket 11.

[0051] The aforementioned tethering element 14 is an elastic element, such as a spring, with one end connected to the locking post 13 and the other end connected to the locking post bracket 11. It is mainly used to hold the locking post 13 in place when it is disengaged and to prevent the locking post 13 from falling off the aircraft.

[0052] like Figure 1BAs shown, the device housing 12 is mounted on the side of the lock column bracket 11 by six fixing bolts, thereby fixing the device housing 12 to the lock column bracket 11.

[0053] Next, refer to Figure 2A and Figure 2B The specific structure of the emergency locking pin release device 1 of the present invention will be described.

[0054] Since the structures of the left and right sides of the lock pillar bracket 11 of the emergency lock pillar release device 1 of the present invention are completely symmetrical, the following description will only take the structure of the left side as an example.

[0055] like Figure 2A As shown, the emergency locking pin release device 1 of the present invention also has an active space inside the device housing 12, in which an active top block 12a, an elastic element 12b, an electromagnet 12c, a connecting block 12d, and a lubrication port 12e are provided.

[0056] The aforementioned active top block 12a is roughly rectangular in shape and is mainly made of magnetizable metal materials such as iron-nickel alloy, carbon steel, and martensitic stainless steel.

[0057] The aforementioned elastic element 12b is disposed within the device housing 12 between the movable top block 12a and the electromagnet 12d, and is made of a spring or other elastically deformable material. It is primarily used in the initial state (non-energized state). Figure 2A The initial state provides a horizontal upward support force to the movable top block 12a, so that the position of the movable top block 12a is balanced at the height of the central axis of the locking pin 13.

[0058] The electromagnet 12c is disposed inside the device housing 12, separated from the movable top block 12a by the elastic member 12b, and is mainly used to attract the movable top block 12a to move downward by means of electromagnetic effect when energized.

[0059] The aforementioned connecting block 12d is roughly in the shape of a stepped frustum. The bottom surface of the frustum abuts against the movable top block 12a, and the other end face opposite to the bottom surface is embedded in the locking post 13 through the locking post bracket 11. The connecting block 12d is mainly made of non-magnetized metal materials such as austenitic stainless steel and titanium alloy, thereby avoiding displacement caused by being attracted by the electromagnet 12c when energized.

[0060] The aforementioned lubrication port 12e connects the aforementioned active space to the outside and is mainly used to inject lubricating oil from the outside of the device housing 12 into the active space so that the emergency locking pin release device 1 can work more smoothly.

[0061] like Figure 2AAs shown, under normal circumstances when the aircraft landing gear is in the retracted state, the electromagnet 12c of the emergency locking pin release device 1 of the present invention is not energized, and the aforementioned movable top block 12a is connected to the elastic member 12b and balanced on the ground. Figure 2A As shown in the figure, the movable top blocks 12a at the left and right ends of the U-shaped lock post bracket 11 abut against and hold the lock post 13 with the connecting blocks 12d. In other words, the lock post 13 is fixed in the lock post bracket 11 by the connecting blocks 12d at the left and right ends.

[0062] With the locking pin 13 secured in the locking pin bracket 11, the locking hook of the upper lock of the landing gear or cabin door engages with the locking pin 13, thereby keeping the landing gear or cabin door in the retracted position.

[0063] However, when unlocking is required, if the unlocking mechanism of the landing gear upper lock or the cabin door upper lock is mechanically jammed or otherwise abnormal and cannot be unlocked, the emergency lock pin release device 1 of the present invention will automatically detect the unlocked landing gear or cabin door and activate the lock pin release device.

[0064] The following is for reference Figure 3A and Figure 3B The working state of the emergency locking pin release device 1 of the present invention will be described.

[0065] like Figure 3A As shown, after the electromagnet 12c of the emergency locking pin release device 1 is energized, the movable top block 12a made of magnetizable material is attracted by the electromagnetic force generated by the energized electromagnet 12c, as... Figure 3A As indicated by arrow ①, the movable top block 12a compresses the elastic element 12b and moves it toward the electromagnet 12c.

[0066] The number of turns of the electromagnet 12c is set so that the electromagnetic force generated after energization can attract the movable top block 12a to compress the elastic member 12b and move it to a position where it is completely disengaged from the connecting block 12d.

[0067] In addition, such as Figure 3A As shown, the angle θ of the frustum of the connecting block 12d is designed such that the axial component of the force N on the connecting block 12d is greater than the maximum static friction force in the horizontal direction, i.e., along the axis of the frustum.

[0068] In this way, such as Figure 3B As shown, after the electromagnet 12c is energized and the movable top block 12a moves to a position completely disengaged from the connecting block 12d, as Figure 3B As shown by arrow ②, due to the loss of the supporting function of the movable top block 12a, the connecting block 12d will slide towards the movable space side of the device housing 12 under the action of the axial component force.

[0069] When the connecting block 12d moves toward the device housing 12 until it falls completely into the movable space, after the two ends of the locking pin 13 lose the fixation of the connecting block 12d, due to the pulling action of the locking hooks engaged with the locking pin 13, the locking pin 13... Figure 3B As indicated by arrow ③, it moves upward and disengages from the locking column bracket 11, thereby disengaging the locking hook of the upper lock of the hatch or landing gear from the locking column bracket 11, thus allowing the hatch or landing gear to open or lower under the action of gravity.

[0070] Since the tethering element 14 is provided on only one side to secure the locking pin 13, the locking hook of the upper lock of the hatch or landing gear that was originally engaged with the locking pin 13 can slide off the other end of the locking pin 13 where the tethering element 14 is not provided and disengage from the locking pin 13.

[0071] At this point, after the locking pin 13 disengages from the locking pin bracket 11 and the locking hook, as follows: Figure 4 As shown, the detached locking pin 13 is secured by the tether 14 to prevent it from falling off the aircraft.

[0072] Since the emergency locking pin release device 1 of the present invention is a locking pin structure with a locking pin release device, the emergency locking pin release device 1 of the present invention has the functions of conventional locking pins, and will not affect the normal retraction and extension of landing gear or cabin doors, nor will it affect the locking and unlocking functions of the upper lock.

[0073] (Technical effect)

[0074] The emergency locking pin release device 1 of the present invention can release the locking pin from the locking pin bracket by controlling the connection and disconnection of the electromagnetic module, thereby completing the lowering of the landing gear.

[0075] Therefore, the device is not affected by any mechanical jamming in the unlocking mechanism, and because the locking pin 13 can be separated, the locking pin can be automatically disengaged without opening the locking hook, thereby enabling the emergency lowering of the landing gear.

[0076] Furthermore, the emergency locking pin release device 1 of the present invention can also serve as an emergency lowering method when the unlocking of the landing gear upper lock or cabin door upper lock of a civil aircraft fails, thereby effectively improving the safety of aircraft operation.

[0077] Furthermore, the emergency locking pin release device 1 of the present invention has a wide range of applications and can be used in the landing gear system of any civil aircraft with a top lock and locking pin structure. Moreover, the emergency locking pin release device is small in size, light in weight, low in cost, and easy to implement.

[0078] The following is for reference Figure 5 and Figure 6 The control principle of the emergency locking pin release device 1 of the present invention will be explained.

[0079] Figure 5 The control principle of the emergency locking pin release device 1 of the present invention is shown, such as... Figure 5 As shown, the control module of the emergency locking pin release device 1 of the present invention is integrated into the conventional landing gear system control unit, and mainly includes an emergency locking pin release control processing module and an emergency locking pin release electromagnetic activation control module.

[0080] The control module of this invention is integrated into the conventional control unit, eliminating the need for additional equipment, which facilitates system integration and reduces production costs.

[0081] The landing gear system control unit is powered by the aircraft's power system, and conventional landing gear system control units include a normal / backup landing gear retraction control module to control the normal retraction and extension of the landing gear.

[0082] When landing gear needs to be lowered, the landing gear normal / backup retraction control module is activated by sending a landing gear normal / backup lowering switch activation signal to the landing gear system control unit. Under normal circumstances, the landing gear normal / backup retraction control module will control the upper lock of the landing gear door and the upper lock of the landing gear to unlock, and ultimately control the opening of the landing gear door and the lowering of the landing gear.

[0083] Then, after the landing gear normal / backup retraction control module operates, the landing gear door open / close indicator sensor and the landing gear retraction / lowering indicator sensor will detect whether the landing gear door is open and whether the landing gear is lowered, respectively, and transmit the detection results to the landing gear door status calculation module and the landing gear status calculation module, respectively.

[0084] The aforementioned landing gear door status calculation module and landing gear status calculation module analyze the detection results and send them to the control module of the emergency locking pin release device 1 of the present invention.

[0085] After receiving an abnormal signal, the emergency locking pin disengagement control processing module of the present invention determines whether the landing gear door and landing gear have been successfully opened and lowered. If the determination is "no", the action command is sent to the emergency locking pin disengagement electromagnetic activation control module. At this time, the coil of the electromagnet 12c of the emergency locking pin disengagement device 1 of the present invention is energized, so that the locking pin 13 disengages from the locking pin bracket 11, thereby causing the landing gear door and landing gear to disengage from the locking pin respectively, so as to realize the emergency opening of the landing gear door and the emergency lowering of the landing gear.

[0086] like Figure 5 As shown, the landing gear doors mainly include the nose landing gear door, the left main landing gear door, and the right main landing gear door. The landing gear mainly includes the nose landing gear, the left main landing gear, and the right main landing gear.

[0087] Therefore, for the upper locks of the landing gear bay doors, separate devices need to be installed for the nose landing gear bay door lock pin release, the left main landing gear bay door lock pin release, and the right main landing gear bay door lock pin release; for the upper locks of the landing gear, separate devices need to be installed for the nose landing gear lock pin release, the left main landing gear lock pin release, and the right main landing gear lock pin release, so as to realize the emergency opening and emergency lowering functions of each landing gear bay door and landing gear on the aircraft.

[0088] Figure 6 The control flow of the emergency locking pin release device 1 of the present invention is shown, such as... Figure 6 As shown, conventional civil aircraft landing gear systems typically have two unlocking methods: normal deployment and backup deployment. When landing gear needs to be deployed, the normal deployment unlocking system is activated first. If normal deployment fails, the pilot will activate the backup deployment unlocking system.

[0089] After receiving the activation signal for the backup to be lowered, the emergency locking pin release control processing module of the present invention, after a confirmation period of 1, determines whether the landing gear doors are fully open via sensors and the landing gear door status calculation module. If it is determined that the landing gear doors are not fully open, the module identifies the closed doors and activates their emergency locking pin release device, causing the locking pin to automatically release, thereby allowing the doors to open automatically under the action of gravity.

[0090] Then, after a confirmation period of 2, the sensors and landing gear status calculation module determine whether the landing gear is fully deployed. If it is determined that the landing gear is not fully deployed, the system identifies the landing gear that is not deployed and activates its emergency locking pin release device, causing the locking pin to automatically release, so that the landing gear is automatically deployed under the action of gravity.

[0091] Among them, confirmation time 1 and confirmation time 2 are the maximum values ​​of the door opening time and the landing gear lowering time, respectively, under all operating conditions of the flight path.

[0092] By using the control method of the emergency locking pin release device 1 of the present invention, it is possible to automatically identify the hatch and landing gear that have failed to unlock and control their locking pins to release, thereby effectively reducing the dangerous situation of landing gear not being able to be lowered due to mechanical jamming.

[0093] Furthermore, the control method based on judgment criteria can make the locking pin disengagement control more precise and reduce the probability of misjudgment and incorrect judgment. Moreover, this control method only receives the door and landing gear status signals and will not affect the landing gear retraction and extension or the door opening and closing control.

[0094] While the structure and working principle of the present invention have been described above in conjunction with preferred embodiments, those skilled in the art should recognize that the above examples are merely illustrative and do not constitute a limitation of the invention. Modifications and variations can be made to the invention within the spirit and scope of the claims, and all such modifications and variations will fall within the protection scope of the present invention.

[0095] For example, in this invention, an example is shown where the structures of the device housings 12 on the left and right sides of the lock pillar bracket 11 of the emergency lock pillar release device 1 of the present invention are completely symmetrical and identical. However, the present invention is not limited to this. The device housing 12 may be provided on only one side, and the abutment structure may be simply provided on the other side, as long as it is convenient for the lock pillar 13 to be released when the electromagnet is energized.

[0096] For example, in this invention, an example is shown in which an electromagnet 12c is provided in the emergency lock release device 1 of the present invention and the lock release is achieved by using electromagnetic effect. However, the present invention is not limited to this, and other actuation structures can also be provided, as long as they can achieve emergency release of the lock.

[0097] For example, in this invention, an example is shown where the movable top block 12a of the emergency locking pin release device 1 is formed into a stepped frustum shape and the connecting block 12d is formed into a cuboid shape. However, this invention is not limited to this and can also be formed into other shapes, as long as the corresponding emergency release function can be achieved.

Claims

1. An emergency locking pin release device (1) capable of releasing a locking pin (13) engaged with a cabin door or landing gear upper lock, characterized in that, include: Locking post bracket (11), the locking post bracket (11) is U-shaped and includes a pair of vertical legs in the vertical direction and a horizontal leg in the horizontal direction; The device housing (12) is fixed to the vertical foot of the locking column bracket (11) by mounting feet and has an internal space for movement. A locking pin (13) is fitted between a pair of vertical legs of the locking pin bracket (11) and abuts against a movable top block (12a) inside the device housing (12) via a connecting block (12d). When the movable top block (12a) moves to a position completely separated from the connecting block (12d) under the action of external force, the connecting block (12d) automatically moves into the movable space under the action of axial pressure and separates from the locking pin (13), and the locking pin (13) disengages from the pair of vertical feet.

2. The emergency locking pin release device (1) as described in claim 1, characterized in that, It also includes a tethering member (14), one end of which is connected to the locking post bracket (11) and the other end of which is connected to the locking post (13).

3. The emergency locking pin release device (1) as described in claim 1 or 2, characterized in that, An electromagnet (12c) is installed within the activity space. The movable top block (12a) is made of a magnetizable metal material, while the connecting block (12d) is made of a non-magnetizable metal material.

4. The emergency locking pin release device (1) as described in claim 3, characterized in that, The electromagnet (12c) abuts against the movable top block (12a) through the elastic member (12b). When the electromagnet (12c) is energized, the movable top block (12a) is attracted to move towards the side of the elastic member (12b) by means of electromagnetic effect.

5. The emergency locking pin release device (1) as described in claim 4, characterized in that, A lubrication port (12e) communicating with the active space is provided on the device housing (12). Lubricating oil is injected into the active space from the outside of the device housing (12) through the lubrication port (12e).

6. The emergency locking pin release device (1) as described in claim 1, characterized in that, The connecting block (12d) is in the shape of a stepped frustum, with the bottom surface of the frustum abutting against the movable top block (12a), and the other end face opposite to the bottom surface being embedded into the locking post (13) via the locking post bracket (11).

7. The emergency locking pin release device (1) as described in claim 6, characterized in that, The angle of the frustum of the connecting block (12d) is designed such that the axial component of the force on the connecting block (12d) is greater than the maximum static friction force at the contact surface that contacts the locking column bracket (11).

8. The emergency locking pin release device (1) as described in claim 1, characterized in that, The device housing (12) is symmetrically arranged on one of the pair of vertical legs of the locking column bracket (11), or is arranged on only one of the pair of vertical legs of the locking column bracket (11).

9. An emergency lock cylinder disengagement control method, capable of disengaging the lock cylinder when normal and backup unlocking fail, the emergency lock cylinder disengagement control method being used to control the emergency lock cylinder disengagement device (1) according to any one of claims 1 to 8, characterized in that, After activating the normal disconnect signal and the backup activation signal. After a period of confirmation, the system uses signals from the landing gear door status calculation module to determine whether all landing gear doors are open. If the determination is "no", the system identifies the closed doors and activates the emergency release device of the door locking pin. If it is determined that all landing gear doors are open, after a confirmation period, the system uses signals from the landing gear status calculation module to determine whether the landing gear is fully deployed. If the determination is "no", the system identifies the undeployed landing gear and activates the emergency disengagement device of the landing gear locking column until it is determined that the landing gear is fully deployed.

10. The emergency locking pin release control method as described in claim 9, characterized in that, The landing gear door opening / closing indicator sensor identifies the opening and closing status of the door and sends the signal to the landing gear door status calculation module. The landing gear retraction / extension indicator sensor identifies the retraction / extension status of the landing gear and sends the signal to the landing gear status calculation module.

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