Emergency lock column separating device and control method thereof

Abstract

The invention discloses an emergency lock cylinder separating device and a control method thereof, and the emergency lock cylinder separating device comprises a U-shaped lock cylinder support which comprises a pair of vertical feet in the vertical direction and a horizontal foot in the horizontal direction; the device shell is fixed on the vertical leg of the lock column bracket through a mounting leg, and a movable space is formed in the device shell; the lock column is embedded between a pair of vertical feet of the lock column support and abuts against a movable ejector block in the device shell across a connecting clamping block, and when the movable ejector block moves to the position where the movable ejector block is completely separated from the connecting clamping block under the action of external force, the movable ejector block can move to the position where the movable ejector block is completely separated from the connecting clamping block; the connecting clamping block automatically moves into the movable space under the action of axial pressure and is separated from the lock column, and the lock column is separated from the position between the pair of vertical feet. According to the emergency lock column disengaging device and the control method thereof, normal putting down of the undercarriage can be guaranteed when mechanical jamming happens to the uplock of the undercarriage.

Description

Technical Field

[0001] The present invention relates to an emergency lock column disengagement device and a control method thereof, and more specifically, to an emergency lock column disengagement device capable of realizing emergency lowering of an aircraft landing gear and a control method thereof. Background Art

[0002] The landing gear is an important load-bearing and maneuverable component of an aircraft, and it plays an extremely important role in the safe take-off and landing of the aircraft.

[0003] The landing gear of an aircraft is a necessary support system for the aircraft to take off, land, taxi, move on the ground and park, and is an important component of the aircraft. It is mainly used to support the aircraft during takeoff, landing or ground taxiing and to move on the ground during this process.

[0004] Specifically, the landing gear plays a role in supporting, cushioning and ground steering when the aircraft lands. The landing gear device usually has two operating states: retracted and lowered. When the landing gear device is in the retracted state, the landing gear upper lock fixes the landing gear in the retracted position, and the cabin door upper lock fixes the cabin door in the closed position; when the landing gear device is in the lowered state, the lock hooks of the landing gear upper lock and the cabin door upper lock will open, and the landing gear will be lowered after the cabin door is opened.

[0005] Usually, the "lock hooks" of the landing gear uplock and the cabin door uplock engage with the "locking posts" on the landing gear and the cabin door structures to achieve the uplock of the landing gear and the cabin door. If the landing gear cannot be lowered due to some faults, this will have a significant negative impact on the safety of the aircraft.

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

[0007] However, the above unlocking methods are all based on mechanical transmission to open the lock hook of the upper lock. When mechanical jamming occurs, for example, mechanical jamming occurs between the lock hook of the upper lock and the lock column, or the unlocking mechanism of the lock hook of the upper lock is jammed, at this time, if the above unlocking methods are used, no matter hydraulic unlocking, electronic unlocking, or cable unlocking, the lock hook of the upper lock cannot be opened to lower the landing gear. Therefore, the above unlocking methods have a "single point failure" of mechanical jamming, which leads to a dangerous failure event that the landing gear cannot be lowered.

[0008] Therefore, it is desirable to provide an emergency lock column disengagement device and a control method thereof, which can ensure the normal lowering of the landing gear when the upper lock of the landing gear is mechanically blocked. Summary of the invention

[0009] The present invention is made to solve the above-mentioned technical problems, and its purpose is to provide an emergency lock column disengagement device and a control method thereof, 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 stuck.

[0010] In order to achieve the purpose of the present invention, an emergency lock column disengagement device is provided, which can disengage the lock column engaged with the upper lock of the cabin door or the landing gear, comprising: a lock column bracket, the lock column bracket is U-shaped, and includes a pair of vertical feet along the vertical direction and a horizontal foot along the horizontal direction; a device shell, the device shell is fixed to the vertical feet of the lock column bracket by mounting feet, and a movable space is formed inside; a lock column, the lock column is embedded between the pair of vertical feet of the lock column bracket, and abuts against the movable top block in the device shell through a connecting block, when the movable top block moves to a position completely separated from the connecting block under the action of external force, the connecting block automatically moves into the movable space under the action of axial pressure and separates from the lock column, and the lock column disengages from between the pair of vertical feet.

[0011] According to the structure as described above, through the emergency lock column disengagement device of the present invention, the lock column can be separated from the lock column bracket connected to the landing gear / landing gear door, and the upper lock hook engaged with the lock column can be separated from the landing gear / landing gear door. In the event of mechanical obstruction of the upper lock, emergency disengagement of the lock column can be achieved, thereby ensuring the normal opening of the door and the normal lowering of the landing gear.

[0012] Preferably, it further comprises a tying piece, one end of the tying piece is connected to the lock column bracket, and the other end is connected to the lock column.

[0013] According to the above-described configuration, by providing the anchoring member, the lock post can be pulled when the lock post is detached, thereby preventing the lock post from falling off the aircraft.

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

[0015] Preferably, the electromagnet contacts the movable top block via an elastic member, and when the electromagnet is energized, the movable top block is attracted to move toward the elastic member by electromagnetic effect.

[0016] According to the above-mentioned structure, the electromagnetic effect generated when the electromagnet is energized can attract the movement of the movable top block, thereby realizing the emergency release of the lock cylinder.

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

[0018] According to the above-mentioned structure, the lubricating oil is injected into the movable space from the outside of the device housing through the lubrication port, so that the emergency lock cylinder release device can operate more smoothly.

[0019] Preferably, the connection block is in the shape of a stepped truncated cone, the bottom surface of the truncated cone abuts against the movable top block, and the other end surface opposite to the bottom surface passes through the lock column bracket and is embedded in the lock column.

[0020] Preferably, the angle of the truncated cone of the connecting block is designed so that the axial force acting on the connecting block is greater than the maximum static friction force at the contact surface with the locking column bracket.

[0021] According to the structure as described above, after the electromagnet is energized and the movable top block moves to a position completely disengaged from the connecting block, the connecting block will automatically slide toward one side of the movable space of the device shell under the action of axial pressure to achieve the disengagement of the lock column. The structure is simple and the operation is convenient.

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

[0023] According to the structure as described above, by symmetrically arranging the device housing and its internal components on a pair of vertical feet of the lock column bracket, the stability of the disengagement device can be ensured through redundant design; by only arranging it on one vertical foot, the structure can be simplified and production and manufacturing costs can be saved.

[0024] In view of the above-mentioned emergency lock column disengagement device, the present invention also provides an emergency lock column disengagement control method, which can realize the disengagement of the lock column when the normal and backup unlocking fail. After activating the normal lowering signal and the backup lowering signal, after a period of confirmation time, the signal from the landing gear door status solution module is used to determine whether the landing gear doors are all opened. If the judgment is "no", the unopened doors are identified, and the emergency disengagement device of the door lock column is started; if it is judged that the landing gear doors are all open, after a period of confirmation time, the signal from the landing gear status solution module is used to determine whether the landing gear is fully lowered. If the judgment is "no", the unlowered landing gear is identified, and the emergency disengagement device of the landing gear lock column is started until it is judged that the landing gear is fully lowered.

[0025] Preferably, the opening / closing state of the door is identified by a landing gear door open / close indication sensor, and a signal is sent to the above-mentioned landing gear door state solution module; the retraction / detraction state of the landing gear is identified by a landing gear retraction / detraction indication sensor, and a signal is sent to the above-mentioned landing gear state solution module.

[0026] According to the above-described structure, when the upper lock of the landing gear or the door is mechanically blocked, the landing gear can be lowered in an emergency or the door can be opened in an emergency, thereby ensuring the safe landing of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] With reference to the above purposes, the technical features of the present invention are clearly described in the following technical scheme, and its advantages are obvious from the following detailed description with reference to the accompanying drawings, which show preferred embodiments of the present invention by way of example without limiting the scope of the inventive concept.

[0028] Figure 1A is a plan view of the emergency lock cylinder release device of the present invention when viewed from the front, Figure 1B This is a plan view when viewed from the side.

[0029] Figure 2A is a partial cross-sectional view of the emergency lock cylinder release device of the present invention when viewed from the front, Figure 2B yes Figure 1A A cross-sectional view taken from section AA.

[0030] Figure 3A and Figure 3B They are respectively working principle diagrams of the lock cylinder disengagement process of the emergency lock cylinder disengagement device of the present invention.

[0031] Figure 4 It is a schematic diagram of the state of the emergency lock cylinder disengaging device of the present invention after the lock cylinder is disengaged.

[0032] Figure 5 It is a control system architecture diagram of the emergency lock column disengagement device of the present invention.

[0033] Figure 6 It is a control flow chart of the control method of the emergency lock column disengagement device of the present invention. Explanation of symbols

[0034] 1 Emergency lock cylinder release device; 11 Locking column bracket; 12 device housing; 12a movable top block; 12b elastic member; 12c Electromagnet; 12d connecting card block; 12e Lubrication port; 13 Locking post; 14 Tie-downs. DETAILED DESCRIPTION

[0035] Embodiments of the present invention will now be described in detail, examples of which are shown in the accompanying drawings. Although the present invention is described in conjunction with exemplary embodiments, it should be appreciated that this specification is not intended to limit the present invention to the exemplary embodiments described below. On the contrary, the present invention is intended to cover not only the exemplary embodiments, but also various alternative forms, modifications, equivalent forms and other embodiments that may be included within the spirit and scope of the present invention as defined by the appended claims.

[0036] Below, refer to Figure 1A and Figure 1B , the overall structure of the emergency lock column disengagement device 1 of the present invention is described.

[0037] like Figure 1A As shown, the emergency lock cylinder disengagement device 1 of the present invention mainly comprises a lock cylinder bracket 11 , a pair of device housings 12 , a lock cylinder 13 and a tethering member 14 .

[0038] The lock column bracket 11 is roughly U-shaped and includes a pair of vertical feet along the vertical direction and a horizontal foot along the horizontal direction. It is mainly used for installing the device housing 12 and the lock column 13, and the base of the lock column bracket 11, that is, the horizontal foot, is fixedly connected to the cabin door or landing gear.

[0039] The pair of device housings 12 are substantially in the shape of a letter "π", each having a mounting foot extending to both sides, and are separately mounted on a pair of vertical feet of the lock column bracket 11.

[0040] The lock column 13 is cylindrical in shape and is overall engaged between a pair of vertical legs of the U-shaped lock column bracket 11 .

[0041] The above-mentioned mooring member 14 is an elastic member, such as a spring, one end of which is connected to the lock column 13 and the other end is connected to the lock column bracket 11. It is mainly used to pull the lock column 13 when the lock column 13 is disengaged and prevent the lock column 13 from falling from the aircraft.

[0042] like Figure 1B As shown, the device housing 12 is fixed to the lock column bracket 11 by six fixing bolts to fix the mounting feet of the device housing 12 to the side of the lock column bracket 11 , thereby fixing the device housing 12 to the lock column bracket 11 .

[0043] Next, refer to Figure 2A and Figure 2B , the specific structure of the emergency lock column disengagement device 1 of the present invention is described.

[0044] Since the structures of the left and right sides of the lock cylinder bracket 11 of the emergency lock cylinder disengaging device 1 of the present invention are completely symmetrical, only the structure of the left side is used as an example for description below.

[0045] like Figure 2A As shown, the emergency lock cylinder disengaging device 1 of the present invention is further provided with an activity space in the device housing 12, in which a movable top block 12a, an elastic member 12b, an electromagnet 12c, a connecting block 12d and a lubrication port 12e are provided.

[0046] The movable top block 12a is substantially in the shape of a rectangular parallelepiped and is mainly made of a magnetizable metal material such as an iron-nickel alloy, carbon steel, or martensitic stainless steel.

[0047] The elastic member 12b is disposed between the movable top block 12a and the electromagnet 12d in the device housing 12 and is made of a material capable of elastic deformation such as a spring. It is mainly used in the initial state (no power supply state, Figure 2A The state is the initial state) to provide a horizontal upward supporting force for 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 lock column 13.

[0048] The electromagnet 12c is disposed in the device housing 12 opposite to the movable top block 12a via the elastic member 12b, and is mainly used to attract the movable top block 12a to move downward by utilizing the electromagnetic effect when power is supplied.

[0049] The above-mentioned connecting block 12d is roughly in the shape of a stepped cone, the bottom surface of which is in contact with the movable top block 12a, and the other end surface opposite to the bottom surface is embedded in the lock column 13 through the lock column bracket 11. The connecting block 12d is mainly made of austenitic stainless steel, titanium alloy and other non-magnetizable metal materials, thereby avoiding being attracted and displaced by the electromagnet 12c when power is turned on.

[0050] The lubrication port 12e connects the activity space with the outside and is mainly used to inject lubricating oil from the outside of the device housing 12 into the activity space so that the emergency lock column disengagement device 1 can work more smoothly.

[0051] like Figure 2A As shown, under normal circumstances when the aircraft landing gear is in the retracted state, the electromagnet 12c of the emergency lock column release device 1 of the present invention is not energized, and the above-mentioned movable top block 12a is connected to the elastic member 12b and balanced at Figure 2A The position is shown, and the movable top blocks 12a at the left and right ends of the U-shaped lock column bracket 11 abut against the connecting block 12d and support the lock column 13, that is, the lock column 13 is fixed in the lock column bracket 11 by the connecting block 12d at the left and right ends.

[0052] When the lock post 13 is fixed in the lock post bracket 11 , the lock hook of the upper lock of the landing gear or the cabin door is engaged with the lock post 13 , thereby keeping the landing gear or the cabin door in the retracted state.

[0053] However, when unlocking is required, if the unlocking mechanism of the landing gear upper lock or the cabin door upper lock is mechanically blocked or other abnormal conditions occur and cannot be unlocked, the emergency lock column disengagement device 1 of the present invention will automatically detect the unlocked landing gear or cabin door and start the lock column disengagement device.

[0054] Below, refer to Figure 3A and Figure 3B , the working state of the emergency lock column disengagement device 1 of the present invention is described.

[0055] like Figure 3A As shown, after the electromagnet 12c of the emergency lock cylinder 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 shown in FIG. Figure 3A As shown by the arrow ① in FIG. 1 , the movable top block 12a compresses the elastic member 12b and moves toward the electromagnet 12c.

[0056] The number of turns of the electromagnet 12c is set so that the electromagnetic force generated after power-on can attract the movable top block 12a to compress the elastic member 12b and move it to a position completely separated from the connecting block 12d.

[0057] In addition, if Figure 3A As shown, the angle θ of the truncated cone of the connecting block 12d is designed so that the axial component of the force N on the connecting block 12d is greater than the maximum static friction force on the connecting block 12d in the horizontal direction, that is, along the axial direction of the truncated cone.

[0058] In this way, if Figure 3B As shown, after the electromagnet 12c is energized and the movable top block 12a is moved to a position completely separated from the connecting block 12d, as shown in FIG. Figure 3B As shown by arrow ② in FIG. 1 , due to the loss of the supporting function of the movable top block 12a, the connecting block 12d will slide toward the active space side of the device housing 12 under the action of the axial component force.

[0059] When the connecting block 12d moves toward the device housing 12 and completely falls into the active space, after the two ends of the lock column 13 lose the fixation of the connecting block 12d, due to the pulling effect of the lock hooks engaged with the lock column 13, the lock column 13 is Figure 3B As shown by the arrow ③ in the figure, it moves upward and disengages from the lock column bracket 11, so that the lock hook of the upper lock of the door or the landing gear is disengaged from the lock column bracket 11, thereby the door or the landing gear is opened or lowered under the action of gravity.

[0060] Since the tie-down piece 14 is only provided on one side to fasten the lock column 13, the lock hook of the upper lock of the door or landing gear originally engaged with the lock column 13 can slide off from the other end of the lock column 13 where the tie-down piece 14 is not provided and disengage from the lock column 13.

[0061] At this time, after the lock column 13 is separated from the lock column bracket 11 and the lock hook, Figure 4 As shown, the detached lock post 13 is tied by a tether 14 to prevent the lock post 13 from falling off the aircraft.

[0062] Since the emergency lock column disengaging device 1 of the present invention is a lock column structure with a lock column disengaging device, the emergency lock column disengaging device 1 of the present invention has the functions of the previous lock columns, and will not affect the normal retraction and lowering of the landing gear or the cabin door, nor will it affect the locking and unlocking functions of the upper lock.

[0063] (Technical Effect)

[0064] Through the emergency lock column disengagement device 1 of the present invention, the lock column and the lock column bracket can be disengaged by controlling the on and off of the electromagnetic module, thereby completing the lowering of the landing gear.

[0065] Therefore, the device can be unaffected by mechanical blocking of any link of the unlocking mechanism, and because the lock column 13 is separated, the lock column can be automatically disengaged without opening the lock hook, thereby realizing emergency lowering of the landing gear.

[0066] In addition, the emergency lock column disengagement device 1 of the present invention can also be used as an emergency lowering method when the unlocking of the landing gear upper lock or the cabin door upper lock of the civil aircraft fails, thereby effectively improving the safety of aircraft operation.

[0067] In addition, the emergency lock column disengagement device 1 of the present invention has a wide range of applications and can be used in any landing gear system of a civil aircraft having an upper lock and a lock column structure. The emergency lock column disengagement device is small in size, light in weight, low in cost, and easy to implement.

[0068] Below, refer to Figure 5 and Figure 6 , the control principle of the emergency lock column disengagement device 1 of the present invention is explained.

[0069] Figure 5 The control principle of the emergency lock column release device 1 of the present invention is shown as follows: Figure 5 As shown, the control module of the emergency lock column disengagement device 1 of the present invention is integrated into the conventional landing gear system control unit, and mainly includes an emergency lock column disengagement control processing module and an emergency lock column disengagement electromagnetic activation control module.

[0070] The control module of the present invention is integrated into the conventional control unit without adding any additional equipment, which is beneficial to system integration and reduces production costs.

[0071] The landing gear system control unit is powered by an aircraft power system, and in the past, the landing gear system control unit included a landing gear normal / backup retraction and extension control module to control the normal retraction and extension of the landing gear.

[0072] When the landing gear needs to be lowered, the control module is activated by transmitting a landing gear normal / backup lowering switch activation signal to the landing gear normal / backup retraction and extension control module of the landing gear system control unit. Under normal circumstances, the landing gear normal / backup retraction and extension control module will control the upper lock of the landing gear door and the upper lock of the landing gear to unlock respectively, and ultimately control the opening of the landing gear door and the lowering of the landing gear.

[0073] Then, after the landing gear normal / backup retraction and extension control module operates, the landing gear door open / close indication sensor and the landing gear retraction / lowering indication sensor will respectively detect whether the landing gear door is open and whether the landing gear is lowered, and transmit the detection results to the landing gear door state solution module and the landing gear state solution module respectively.

[0074] The landing gear door state solving module and the landing gear state solving module analyze the detection results and send them to the control module of the emergency lock column disengagement device 1 of the present invention.

[0075] After receiving the abnormal signal, the emergency lock column disengagement control processing module of the present invention determines whether the landing gear door and the landing gear are successfully opened and lowered. When the judgment is "no", the action instruction is sent to the emergency lock column disengagement electromagnetic activation control module. At this time, the coil of the electromagnet 12c of the emergency lock column disengagement device 1 of the present invention is energized, so that the lock column 13 is disengaged from the lock column bracket 11, so that the landing gear door and the landing gear are respectively disengaged from the lock column, so as to realize the emergency opening of the landing gear door and the emergency lowering of the landing gear.

[0076] like Figure 5 As shown, the landing gear doors mainly include a front landing gear door, a left main landing gear door, and a right main landing gear door, and the landing gear mainly includes a front landing gear, a left main landing gear, and a right main landing gear.

[0077] Therefore, for the upper lock of the landing gear door, it is necessary to set the front landing gear door lock column disengagement device, the left main landing gear door lock column disengagement device, and the right main landing gear door lock column disengagement device respectively; for the upper lock of the landing gear, it is necessary to set the front landing gear lock column disengagement device, the left main landing gear lock column disengagement device, and the right main landing gear lock column disengagement device respectively, so as to realize the emergency opening and emergency lowering functions of each landing gear door and landing gear on the aircraft.

[0078] Figure 6 The control flow of the emergency lock column release device 1 of the present invention is shown as follows: Figure 6 As shown, the landing gear system of the previous civil aircraft usually has two unlocking modes: normal lowering and backup lowering. When the landing gear needs to be lowered, the unlocking system for normal lowering is first started. After the normal unlocking fails, the pilot will activate the unlocking system for backup lowering.

[0079] After receiving the backup lowering activation signal, the emergency lock column disengagement control processing module of the present invention determines whether the landing gear doors are fully opened through the sensor and the landing gear door state solution module after a confirmation time 1. If it is determined that the landing gear doors are not fully opened, the unopened doors are identified, and their emergency lock column disengagement devices are activated to automatically disengage the lock columns, so that the doors are automatically opened under the action of gravity.

[0080] Then, after a confirmation time 2, the sensor and the landing gear state solution module determine whether the landing gear is fully lowered. If it is determined that the landing gear is not fully lowered, the landing gear that is not lowered is identified, and its emergency lock column disengagement device is activated and the lock column is automatically disengaged, so that the landing gear is automatically lowered under the action of gravity.

[0081] The above-mentioned confirmation time 1 and confirmation time 2 are respectively the maximum values ​​of the door opening time and the landing gear lowering time under all working conditions of the route.

[0082] By means of the control method of the emergency lock column disengagement device 1 of the present invention, doors and landing gear that fail to be unlocked can be automatically identified, and their lock columns can be controlled to disengage, thereby effectively reducing the dangerous situation in which the landing gear cannot be lowered due to mechanical blocking.

[0083] In addition, the control method based on judgment criteria can make the lock column disengagement control more accurate and reduce the probability of misjudgment and wrong judgment. Moreover, the control method only receives the door and landing gear status signals and will not cause any impact on the landing gear retraction and door opening and closing control.

[0084] Although the structure and working principle of the present invention are described above in combination with the preferred embodiments, those skilled in the art should recognize that the above examples are only for illustration and do not constitute a limitation of the present invention. The present invention can be modified and varied within the spirit of the claims, and these modifications and variations will fall within the protection scope of the present invention.

[0085] For example, in the present invention, an example is shown in which the structures of the device shells 12 on the left and right sides of the lock column bracket 11 of the emergency lock column disengagement device 1 of the present invention are completely symmetrical and identical, but the present invention is not limited to this. The device shell 12 can also be provided on only one side, and a simple abutment structure can be provided on the other side, as long as it is convenient to enable the lock column 13 to be disengaged when the electromagnet is energized.

[0086] For example, in the present invention, an example is shown in which an electromagnet 12c is provided in the emergency lock cylinder disengagement device 1 of the present invention and the electromagnetic effect is used to achieve the disengagement of the lock cylinder, but the present invention is not limited to this, and other actuating structures may also be provided as long as the emergency disengagement of the lock cylinder can be achieved.

[0087] For example, in the present invention, an example is shown in which the movable top block 12a of the emergency lock column disengagement device 1 of the present invention is formed into a stepped truncated cone shape, and the connecting block 12d is formed into a rectangular parallelepiped shape, but the present invention is not limited to this and can also be formed into other shapes as long as the corresponding emergency disengagement function can be achieved.

Claims

1. An emergency lock post disengagement device (1), capable of disengaging a lock post (13) engaged with an upper lock of a door or landing gear, characterized in that: include: A locking column bracket (11), the locking column bracket (11) is U-shaped and comprises a pair of vertical legs along the vertical direction and a horizontal leg along the horizontal direction; A device housing (12), wherein the device housing (12) is fixed to the vertical foot of the lock column bracket (11) through a mounting foot and has a movable space formed inside; A lock column (13), wherein the lock column (13) is embedded between a pair of vertical legs of the lock column bracket (11) and abuts against a movable top block (12a) in 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 and separates from the locking column (13) under the action of axial pressure, and the locking column (13) disengages from between the pair of vertical legs.

2. The emergency lock cylinder release device (1) according to claim 1, characterized in that: It also comprises a tying piece (14), one end of which is connected to the locking column bracket (11), and the other end of which is connected to the locking column (13).

3. The emergency lock cylinder release device (1) according to claim 1 or 2, characterized in that: An electromagnet (12c) is arranged in the activity space. The movable top block (12a) is made of a magnetizable metal material, and the connecting clamp block (12d) is made of a non-magnetizable metal material.

4. The emergency lock cylinder release device (1) according to claim 3, characterized in that: The electromagnet (12c) is in contact with the movable top block (12a) via the elastic member (12b), and when the electromagnet (12c) is energized, the electromagnetic effect is used to attract the movable top block (12a) to move toward the elastic member (12b).

5. The emergency lock cylinder release device (1) according to claim 4, characterized in that: The device housing (12) is provided with a lubrication port (12e) communicating with the activity space, and lubrication oil is injected into the activity space from the outside of the device housing (12) through the lubrication port (12e).

6. The emergency lock cylinder release device (1) according to claim 1, characterized in that: The connecting block (12d) is in the shape of a stepped truncated cone, the bottom surface of which abuts against the movable top block (12a), and the other end surface opposite to the bottom surface passes through the lock column bracket (11) and is embedded in the lock column (13).

7. The emergency lock cylinder release device (1) according to claim 6, characterized in that: The angle of the truncated cone of the connecting block (12d) is designed so that the axial force applied to the connecting block (12d) is greater than the maximum static friction force at the contact surface with the locking column bracket (11).

8. The emergency lock cylinder release device (1) according to claim 1, characterized in that: The device housing (12) is symmetrically arranged on a pair of vertical legs of the locking column bracket (11), or is arranged only on one of the pair of vertical legs of the locking column bracket (11).

9. An emergency lock cylinder disengagement control method, which can realize the disengagement of the lock cylinder when normal and backup unlocking fail, characterized in that: After activating the normal disengagement signal and the backup activation signal, After a period of confirmation time, the signal from the landing gear door state calculation module is used to determine whether the landing gear doors are all opened. If the judgment is "no", the unopened doors are identified and the emergency release device of the door lock column is activated; When it is determined that the landing gear doors are all open, after a period of confirmation time, the signal from the landing gear state solution module is used to determine whether the landing gear is fully lowered. When the judgment is "no", the landing gear that has not been lowered is identified, and the emergency release device of the landing gear lock column is started until it is determined that the landing gear is fully lowered.

10. The emergency lock column disengagement control method according to claim 9, characterized in that: Identify the opening / closing state of the door through the landing gear door opening / closing indication sensor, and send a signal to the landing gear door state solving module; The retraction / extension state of the landing gear is identified by a landing gear retraction / extension indication sensor, and a signal is sent to the landing gear state calculation module.

Images