CN214493348U - Locking clearance eliminating device for airplane locking device - Google Patents

Locking clearance eliminating device for airplane locking device Download PDF

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Publication number
CN214493348U
CN214493348U CN202120317075.8U CN202120317075U CN214493348U CN 214493348 U CN214493348 U CN 214493348U CN 202120317075 U CN202120317075 U CN 202120317075U CN 214493348 U CN214493348 U CN 214493348U
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Prior art keywords
lock
locking
wedge
rocker arm
spring
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CN202120317075.8U
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牛成奎
张士卫
薛小伟
郑红
曾涛
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SICHUAN LINGFENG AVIATION HYDRAULIC MACHINERY CO Ltd
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SICHUAN LINGFENG AVIATION HYDRAULIC MACHINERY CO Ltd
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Abstract

The utility model discloses an aircraft locking ware locking clearance remove device can eliminate the locking clearance automatically, prevents that emitter from taking place to rock. The utility model discloses a following technical scheme realizes: the axial fastening bolt is connected with an unlocking actuating cylinder on the upper inclined plane at the front end of the lock shell of the locking device and a limiting wedge block positioned below the unlocking actuating cylinder, a shifting fork rotating shaft below the bottom of the unlocking actuating cylinder is connected with a shifting fork of an unlocking actuating cylinder actuating rod, a rocker arm rotating shaft penetrating through a lock shell box body of the locking device is movably connected with a rocker arm, the rocker arm extends out of the back end of the lock shell of the locking device, a lock ring is hooked through a lock connected with a parallel spring on a cantilever rotating shaft, a lock hook rotating shaft penetrating through the lock shell box body of the locking device is fixedly connected with support lugs at two sides of the lock shell body of the locking device and penetrates through support lug holes, and a lock spring for restraining the motion of a lock key through the support lugs; the wedge springs are fixedly connected to two sides of the lock shell of the locking device, and the shifting fork on the outer side of the wedge is restrained on the inner side of the spring fixing shaft through the spring fixing shaft connected to the free end to form a clearance eliminating mechanism.

Description

Locking clearance eliminating device for airplane locking device
Technical Field
The utility model relates to an aircraft lock stopper locking clearance remove device of aircraft airborne system emitter.
Background
The transmitting device is an important component of an airborne system of the airplane. The transmitting device forms a complete airborne control system through mechanical, electrical and radio frequency connection. Whether the locking and unlocking of the launching device is reliable or not is directly related to the use of airborne launching, and the launching efficiency is influenced. The interface between the launch device and the aircraft is commonly referred to as the launch device on-board interface, and includes both mechanical and electrical interfaces. At present, 3 types of bolt type, lifting lug type, stopping lug type and fork lug type are required to be mechanically connected on a common airborne launcher. Generally, a type of transmitting device has only one interface. Sometimes, to adapt to different carriers, the transmitting device is required to have the capability of multiple interfaces. The common method is to select an interface as the basic model, and a transfer beam is added on the launching device when the interface is changed. This "two-storey" construction results in a considerable increase in the overall height and weight of the launch apparatus. The performance of the loader is necessarily reduced when the loader flies. With the continuous improvement of the connection requirements of airborne electronic products on electrical appliances and the improvement of the wire outlet requirements at the rear part of airborne equipment, the rear rectangular electric connector is widely applied to the airborne electronic equipment. The front locking device is one of the main structural members of the on-board electronic device to which the rear rectangular connector is mounted. The electronic device structure is generally formed by a chassis and a mounting bracket. Both are generally integrated by front and rear fastening means. The fastening device is composed of a lever latch combined handle (handle component) on the case and a fork rod type positioning piece (hook component) on the mounting frame. The handle component is fixed on the front panel of the case, the case is placed on the mounting frame by loosening the push rod during working, the lower end of the push rod is in contact with a pin shaft of a hook component fixed on the mounting frame, then the push rod is pushed upwards to be locked with the spring component, and the case is locked at the moment; otherwise, the spring leaf in the spring assembly is pushed to make the push rod flick, so that the machine box can be unlocked. When the airplane is accelerated, the inertia force of the airborne aircraft acts on the rear stopper of the locking device, and the situation that the airborne aircraft falls off from the rear due to the lifting of the rear stopper is avoided; when the airplane decelerates, the inertia force of the airborne vehicle acts on the front stop piece of the locking device, and the situation that the airborne vehicle falls off from the front due to the lifting of the front stop piece is avoided. The unlocking force value of the conventionally designed locking device is about 2 times of the weight of the airborne aircraft, the inertial force generated by the airborne aircraft in various take-off and landing conditions can exceed the unlocking force, and particularly, the airborne aircraft can generate overload of more than 7 when the aircraft is blocked by the landing steel cable for forced deceleration. In order to ensure that the aircraft does not fall off the launcher under all circumstances, a mechanical safety mechanism must be provided on the lock, which is required to lock the aircraft in the launcher when in principle even if the engine is fired. Mechanical fuses can be classified into two categories in principle: electromagnetic mechanical insurance. The mechanical fuse is operated by a direct current power supply provided by the aircraft, when the aircraft is not electrified, the mechanical fuse is in a locking state, and the locking device provides a great locking force for the aircraft; after power is on, the mechanical fuse is opened, and the locking force is converted into normal unlocking force. And (4) inertia mechanical insurance. The aircraft launching device adopts an inertia hammer, when the aircraft is not overloaded, a mechanical fuse controlled by the inertia hammer is in an open state, a locking device provides normal unlocking force, when the aircraft is overloaded along the negative course and exceeds a certain value, the inertia hammer swings, and the mechanical fuse is in a locked state, so that the airborne aircraft is kept on the launching device. The electromagnetic mechanical fuse can guarantee that no matter what state the aircraft is in, the locking device can restrain the aircraft-mounted aircraft on the transmitting device as long as no transmitting instruction is given, but the electromagnetic mechanical fuse is relieved and the power supply is supplied by the aircraft. The inertia mechanical type insurance can self-adapt to the overload of the airplane, ensures that the airborne aircraft can not fall off under various flight states, but the action of the inertia mechanical type insurance is influenced by the attitude of the airborne aircraft and the overload duration time, has higher design difficulty and can not meet the requirement that the airborne aircraft is restrained on the launching device when an engine is accidentally ignited. The typical stopper structure of the locking device has two types: an integral stopper. The front blocking piece and the rear blocking piece are designed into one part, the part can rotate around two pivot points, when the bullet is loaded and unloaded, the blocking pieces rotate around the front pivot points by using a spanner to lift the rear blocking pieces, and the airborne aircraft slide block enters between the blocking pieces; when the airborne aircraft launches, the blocking piece rotates around the rear fulcrum to lift the front blocking piece, and the airborne aircraft sliding block smoothly passes through. A separate stopper. The front and rear stoppers are separate and independently movable, the front stopper being rotatable about an axis, and the rear stopper being vertically movable or rotatable about an axis behind. The above two stoppers have the corresponding characteristics that: the integrated stopper is used for preventing an airborne aircraft from falling off from the back of the launching device when the aircraft is subjected to forward overload in the course, an aerial safety pin must be inserted after the airborne aircraft is hung, the rear stopper is prevented from being lifted when stressed, meanwhile, the aerial safety pin cannot prevent the stopper from rotating around a rear pivot, and the structure causes certain difficulty in the design of mechanical safety. If the ignition contacts of the onboard aircraft engine are arranged on the latch, the use of this mechanism will cause the onboard aircraft slider to strike the ignition contacts during loading. Certain gaps are formed between the guide rail and the airborne aircraft sliding block in the vertical and horizontal directions, so that any retardation phenomenon cannot occur in the process of off-orbit. For sequential off-track, the risk of the launch process occurs mainly in the case where the airborne vehicle only has the last slider left, and then if the heading drift angle of the airborne vehicle relative to the launch device is increased to such an extent that the gap between the rear slider of the airborne vehicle and the guide rail is completely consumed, the cartridge rack interference will occur. The electromagnetic mechanical fuse has the same functions on the ground and in the air, and is unlocked when being electrified and locked when being disconnected. If the engine is detained on the aircraft after accidental ignition, the tail wing of the aircraft can be burnt, and a sideslip moment can be caused to the aircraft in the air due to the fact that the hanging position of the aircraft is a certain distance away from the axis of the engine, but the thrust of the engine of the aircraft is much smaller than that of the engine of the aircraft, and the aircraft can still be controlled; ground personnel, friend machines, towers, villages and common people may exist in front of the airplane on the ground, and friend machines may exist in front of the airplane in the air, and if the airborne aircraft is separated from the transmitting device and transmitted, the harm caused is difficult to estimate.
The reliable locking and unlocking of the launching device, which is one of the important devices in the aircraft structure, directly affects the use of the on-board weapons, and it is necessary to ensure sufficient rigidity. At present, most of machine type launching devices are manually locked and unlocked after being lifted in place by a motor, and because the motor cannot ensure that two ends of the launching device simultaneously reach a locking position to complete locking when the launching device is lifted, the locking difficulty and the complexity of the lifting device are increased. After the airplane bears a large aerodynamic load in the flying process, the locking device elastically deforms, and the difficulty of manual unlocking is increased after the clearance is eliminated through the wedge block. In addition, under the condition of ensuring the rigidity requirement of a locking ring of the launching device, the existing locking device cannot meet the requirement of gapless locking, and gapless locking means that no gap exists between the locking mechanism and the locking device after the locking device is locked, so that the locking mechanism can be prevented from shaking in the flying process of an airplane.
SUMMERY OF THE UTILITY MODEL
The utility model aims at the weak point that the traditional locking mode of emitter exists, provide one kind and be applicable to asynchronous locking, can eliminate the locking clearance automatically, prevent that emitter from taking place to rock, integrated signal output to adopt the locking device of gas/hydraulic drive unblock.
The utility model provides a technical scheme that its technical problem adopted is: an aircraft lock brake locking lash take-up device comprising: lock mechanism lock shell 1 through bolt and aircraft organism is connected, connect the actuating cylinder 2 of unblanking and be located the spacing voussoir 6 of unblanking actuating cylinder 2 below at lock mechanism lock shell (1) front end upper portion inclined plane through axial fastening bolt 18, link firmly shift fork pivot 12 and the shift fork 7 that the actuating cylinder 2 actuating rod links to each other of unblanking under the actuating cylinder 2 bottom of unblanking through the pivot, through fastening bolt and the travel switch 13 of lock mechanism lock shell 1 casing inboard solid antithetical couplet, the catch 14 of linking firmly with emitter, its characterized in that: a rocker arm rotating shaft 15 penetrating through the box body of the locking device lock shell 1 is movably connected with a rocker arm 10, the rocker arm 10 extends out of the back end of the locking device lock shell 1, is connected with a lock hook 3 hooking a lock ring 14 through a parallel spring 9 on a cantilever rotating shaft, penetrates through a lock hook rotating shaft 11 of the box body of the locking device lock shell 1, is fixedly connected with support lugs on two sides of the shell body of the locking device lock shell 1 and penetrates through support lug holes, and a lock spring 8 restraining the movement of a lock key 4 through the support lugs; wedge springs 5 fixedly connected to both sides of the lock case 1 are provided, and a shift fork 7 on the outer side of a wedge 6 is restrained on the inner side of the spring fixing shaft through the spring fixing shaft connected to the free end, thereby forming a clearance eliminating mechanism.
The utility model discloses compare and have following beneficial effect in prior art:
the utility model adopts the automatic clearance eliminating mechanism, after being locked, the clearance between the lock ring 14 and the lock stopper lock shell limiting surface 25 is automatically eliminated, the launching device is prevented from shaking in the aircraft flying process, the gapless locking is realized, and after being locked, the lock ring 14 and the height difference of the lock stopper lock shell limiting surface are combined, so that the lock hook 3 can continue to rotate upwards by a certain angle after having the locking capacity, and the asynchronous locking of the airborne launching device is realized; the integrated signal output device is used for outputting a locking in-place signal after locking; when the launching device is put down, the pneumatic/hydraulic unlocking is realized quickly, and the reliability, the safety and the maintainability of the launching device are improved.
Drawings
FIG. 1 is a schematic view of the locking clearance eliminating device of the aircraft locking device of the present invention;
FIG. 2 is a schematic view of the unlocked state of FIG. 1;
FIG. 3 is a schematic view of the locked state of FIG. 1;
FIG. 4 is a schematic view of the gap elimination mechanism of FIG. 1;
FIG. 5 is a schematic illustration of the left and right end lock ring positions of FIG. 1;
FIG. 6 is a schematic view of the one side lock housing of FIG. 1;
in the figure: 1 locking device lock shell, 2 unlocking actuating cylinders, 3 lock hooks, 4 lock keys, 5 wedge springs, 6 wedges, 7 shifting forks, 8 lock springs, 9 parallel springs, 10 rocker arms, 11 lock hook rotating shafts, 12 shifting fork rotating shafts, 13 signal output devices, 14 lock rings, 15 rocker arm rotating shafts, 16 unlocking nozzles, 17 bolt shafts, 18 fastening bolts, 19 wedge block front inclined planes, 20 wedge block rear inclined planes, 21 wedge block limiting planes, 22 left end lock rings, 23 right end lock rings, 24 locking device lock shell built-in slide ways, 25 locking device lock shell limiting planes, 26 rocker arm stop planes, 27 lock hook stop planes, 28 rocker arm supporting planes and 29 lock hook supporting planes.
Detailed Description
See fig. 1-5. In an embodiment described below, an aircraft lock brake lock clearance elimination apparatus includes: the locking device is characterized by comprising a locking device lock shell 1 connected with an airplane body through bolts, an unlocking actuating cylinder 2 connected with an inclined plane at the upper part of the front end of the locking device lock shell (1) through an axial fastening bolt 18, a limiting wedge block 6 positioned below the unlocking actuating cylinder 2, a shifting fork rotating shaft 12 fixedly connected below the bottom of the unlocking actuating cylinder 2 through a rotating shaft and a shifting fork 7 connected with an actuating rod of the unlocking actuating cylinder 2, a travel switch 13 fixedly connected with the inner side of a shell of the locking device lock shell 1 through a fastening bolt and a lock ring 14 fixedly connected with a transmitting device. A rocker arm rotating shaft 15 penetrating through the box body of the locking device lock shell 1 is movably connected with a rocker arm 10, the rocker arm 10 extends out of the back end of the locking device lock shell 1, is connected with a lock hook 3 hooking a lock ring 14 through a parallel spring 9 on a cantilever rotating shaft, penetrates through a lock hook rotating shaft 11 of the box body of the locking device lock shell 1, is fixedly connected with support lugs on two sides of the shell body of the locking device lock shell 1 and penetrates through support lug holes, and a lock spring 8 restraining the movement of a lock key 4 through the support lugs; wedge springs 5 fixedly connected to both sides of the lock case 1 are provided, and a shift fork 7 on the outer side of a wedge 6 is restrained on the inner side of the spring fixing shaft through the spring fixing shaft connected to the free end, thereby forming a clearance eliminating mechanism.
During locking, a lock ring 14 fixedly connected with the launching device collides with a lock hook 3, the lock hook 3 is driven to rotate anticlockwise around a lock hook rotating shaft 11, then a lock key 4 is pushed upwards to overcome a lock spring 8 and move upwards along a lock brake lock shell lug hole, after a lock hook supporting surface 29 is separated from a rocker arm supporting surface 28, a rocker arm 10 rotates anticlockwise to a locking position under the action of a parallel spring 9, the lock ring 14 continues to move upwards to a lock brake lock shell limiting surface 25 and stops, a lock hook stopping surface 27 is attached to a rocker arm stopping surface 26, the lock hook 3 cannot rotate clockwise and is in a locking state, at the moment, a wedge block 6 slides leftwards along a built-in slide way 24 of the lock brake lock shell under the action of a wedge block spring 5, the gap is eliminated, and gapless locking is realized. When the lock is unlocked, air/hydraulic pressure is supplied to the unlocking actuator cylinder 2 provided with the unlocking nozzle 16, a piston rod arranged in the unlocking actuator cylinder 2 pushes a shifting fork 7 to rotate anticlockwise around a shifting fork rotating shaft 12, the shifting fork 7 pushes a wedge block 6 to move rightwards along a slide rail 24 arranged in a lock shell of the lock, then the piston rod arranged in the unlocking actuator cylinder 2 continues to extend out, a rocker arm 10 is pushed to rotate clockwise along a rocker arm rotating shaft 15, after a lock hook stop surface 27 is separated from a rocker arm stop surface 26, the rocker arm 10 pulls a lock hook 3 through a parallel spring 9, and the lock hook 3 rotates clockwise around a lock hook rotating shaft 11 to complete unlocking.
See fig. 2. Unlocking process: when the launching device is put down from the cabin of the airplane, the unlocking action of the locking device is firstly completed, air/hydraulic pressure is supplied to the unlocking actuating cylinder 2 provided with an unlocking nozzle 16, the air/hydraulic pressure enters the unlocking actuating cylinder 2 from the unlocking nozzle 16, a piston rod arranged in the unlocking actuating cylinder 2 firstly pushes a bolt shaft 17 to push a shifting fork 7 to rotate anticlockwise around a shifting fork rotating shaft 12, the shifting fork 7 pushes a wedge block 6 to slide rightwards along a slide way 24 arranged in a lock shell of a lock stopper, then a piston rod arranged in the unlocking actuating cylinder 2 continuously pushes a rocker arm 10 to rotate clockwise around a rocker arm rotating shaft 15, when the rocker arm 10 is rotated to be separated from a stop surface of a locking hook 3, the locking hook 3 rotates clockwise around a locking hook rotating shaft 11 under the gravity of a parallel spring 9 and the launching device, when the locking hook 3 rotates for a certain angle, a locking ring 14 slides out of the locking hook 3, the launching device completes the putting down action under the action of a lifting motor, and stops supplying pressure to the unlocking nozzle 16, the unlocking actuator cylinder 2 finishes retraction action under the action of a built-in spring, simultaneously pulls back the shifting fork 7 to remove the limitation on the wedge 6, the wedge 6 slides leftwards along the lock case 1 of the locking device with a slideway under the action of the wedge spring 5, when the wedge slides to the position of the lock key 4, the wedge limiting surface 21 is limited by the lock key 4 and cannot slide leftwards continuously, so that the next time the lock ring 14 impacts the lock hook 3 to finish locking action, and the whole unlocking process is finished.
See fig. 3. The two sides of the aircraft cabin are respectively provided with 1 locking device, the lifting of the launching device is completed by 1 set of lifting motor, and the locking is completed by the locking devices after the launching device is lifted in place. The locking process is described below by taking the left end of the launching device first lifted in place as an example: when the launching device is lifted to an airplane bomb compartment from the ground, the left end of the launching device is firstly in place along with the lifting of the launching device, then the left end lock ring 22 fixedly connected to the launching device firstly collides with the lock hook 3 of the left end locking device, and drives the lock hook 3 to rotate anticlockwise around the lock hook rotating shaft 11, when the left end lock ring is rotated until the lock hook supporting surface 29 is separated from the rocker arm supporting surface 28, the rocker arm 10 rotates anticlockwise to a locking position under the action of the parallel spring 9, the rocker arm 10 triggers the signal output device to output a locking signal, at the moment, the left end locking device has locking capacity, along with the continuous upward lifting of the launching device, the left end lock ring 22 pushes the lock key 4 to overcome the lock spring 8 to move upwards, when the lock key 4 moves upwards to be separated from the wedge block limiting surface 21, the wedge block 6 moves leftwards under the action of the wedge block spring 5, the wedge block front inclined surface 19 contacts with the left end lock ring 22 and then slides rightwards in the opposite direction, along with the continuous upward movement of the left end lock ring 22, the right end locking ring 23 completes right end locking according to a phase synchronization step, after the left end locking ring 22 moves to the lock stopper lock shell limiting surface 25, the left end locking ring 22 is limited by the lock stopper lock shell 1 and cannot move upwards continuously, the lifting motor stops lifting (the right end locking ring 23 does not need to move to the lock stopper lock shell 1 and has locking capacity), then the lifting motor reverses, the launching device provided with the locking ring 14 is put down, the locking hook 3 is driven to rotate clockwise around the locking hook rotating shaft 11, when the locking surface of the locking hook 3 is in contact with the locking surface of the rocker arm 10, the locking hook 3 cannot rotate clockwise around the locking hook rotating shaft 11 continuously, the locking ring 14 is hooked by the locking hook 3 and cannot be put down continuously, the lifting motor stops working, and the whole locking process is completed.
See fig. 4. The clearance eliminating mechanism mainly comprises a lock key 4 provided with a lock spring 8 and a wedge 6 hung with a wedge spring 5, wherein the front end of the wedge 6 is provided with a wedge limiting surface 21 with a sunken step, a front inclined surface 19 and a wedge rear inclined surface 20 which are positioned below the wedge limiting surface, the wedge angle of the wedge front inclined surface 19 is larger than an arctangent function arctan mu, the wedge angle of the wedge rear inclined surface 20 is smaller than or equal to the arctangent function arctan mu, and mu is a friction coefficient between the wedge 6 and a lock shell limiting surface 25 of the lock. The method is characterized in that: after locking, when there is a gap between the lock ring 14 and the stopper surface 25 of the lock housing of the lock, the wedge 6 automatically slides to the left by the wedge spring 5, and the gap is eliminated by the wedge rear slope 20. After unlocking, the lock ring 14 is put down along with the launching device, the limitation on the lock key 4 is removed, the lock key 4 moves downwards under the action of the lock spring 8 to be in contact with the wedge limiting surface 21, the wedge 6 is limited to continue sliding leftwards, and the situation that the lock ring 14 is hindered to lift during next locking and locking cannot be completed is prevented.
The foregoing is directed to the preferred embodiment of the present invention, and it is noted that the above-mentioned embodiments illustrate rather than limit the invention, and that those skilled in the art will be able to design alternative embodiments without departing from the scope of the appended claims. It will be apparent to those skilled in the art that various modifications and improvements can be made without departing from the spirit and substance of the invention, and these modifications and improvements are also considered to be within the scope of the invention.

Claims (9)

1. An aircraft lock brake locking lash take-up device comprising: lock mechanism lock shell (1) through bolt and aircraft organism be connected, connect the actuating cylinder (2) of unblanking on lock mechanism lock shell (1) front end upper portion inclined plane and be located spacing voussoir (6) of unblanking actuating cylinder (2) below through axial fastening bolt (18), link firmly shift fork pivot (12) and the shift fork (7) that actuating cylinder (2) actuating rod links to each other of unblanking actuating cylinder (2) bottom below through the pivot, through travel switch (13) that fastening bolt and lock mechanism lock shell (1) casing inboard linked firmly, catch (14) with emitter linked firmly, its characterized in that: a rocker arm rotating shaft (15) penetrating through a box body of the locking device lock shell (1) is movably connected with a rocker arm (10), the rocker arm (10) extends out of the back end of the locking device lock shell (1), a lock hook (3) hooking a lock ring (14) is connected through a parallel spring (9) on a cantilever rotating shaft, the rocker arm penetrates through a lock hook rotating shaft (11) of the box body of the locking device lock shell (1), support lugs fixedly connected to two sides of a shell body of the locking device lock shell (1) and penetrate through support lug holes, and a lock spring (8) restraining the movement of a lock key (4) through the support lugs; wedge springs (5) fixedly connected to two sides of a shell of the lock shell (1) of the locking device restrain a shifting fork (7) on the outer side of a wedge (6) on the inner side of a spring fixing shaft through the spring fixing shaft connected to the free end to form a clearance eliminating mechanism.
2. An aircraft lock brake lock clearance relief arrangement according to claim 1, wherein: a piston rod arranged in an unlocking actuator cylinder (2) firstly pushes a bolt shaft (17) to push a shifting fork (7) to rotate anticlockwise around a shifting fork rotating shaft (12), the shifting fork (7) pushes a wedge block (6) to slide rightwards along a slide way (24) arranged in a lock shell of a locking device, the piston rod continuously pushes a rocker arm (10) to rotate clockwise around a rocker arm rotating shaft (15), the rocker arm (10) rotates to be separated from a locking surface of a locking hook (3), the locking hook (3) rotates clockwise around the locking hook rotating shaft (11) under the action of a parallel spring (9) and the gravity of a transmitting device, after the locking hook (3) rotates for a certain angle, a locking ring (14) slides out of the locking hook (3), and the transmitting device completes the lowering action under the action of a lifting motor.
3. An aircraft lock brake lock clearance relief arrangement according to claim 2, wherein: after the pressure supply is stopped, the unlocking actuator cylinder (2) finishes the retraction action under the action of a built-in spring, simultaneously pulls back the shifting fork (7) to remove the limitation on the wedge block (6), the wedge block (6) slides leftwards along the lock shell (1) of the lock brake with the slide way under the action of the wedge block spring (5), when the wedge block slides to the position of the lock key (4), the wedge block limiting surface (21) is limited by the lock key (4) and cannot slide leftwards continuously, and the locking action is finished.
4. An aircraft lock brake lock clearance relief arrangement according to claim 1, wherein: the clearance elimination mechanism includes: the wedge locking mechanism comprises a locking key (4) provided with a locking spring (8), a wedge block (6) hung with a wedge block spring (5), and a wedge block limiting surface (21) with a sunken step, a front inclined surface (19) and a wedge block rear inclined surface (20) which are positioned below the front end of the wedge block (6).
5. An aircraft lock brake lock clearance relief arrangement according to claim 4, wherein: the wedge angle of the wedge front inclined surface (19) is larger than the arctangent function arctan mu, the wedge angle of the wedge rear inclined surface (20) is not larger than the arctangent function arctan mu, and mu is the friction coefficient between the wedge (6) and the lock shell limiting surface (25) of the lock.
6. An aircraft lock brake lock clearance relief arrangement according to claim 1, wherein: the wedge block (6) automatically slides leftwards under the action of the wedge block spring (5), and pushes the rear inclined surface (20) of the wedge block to eliminate the gap.
7. An aircraft lock brake lock clearance relief arrangement according to claim 1, wherein: after the lock is unlocked, the lock ring (14) is put down along with the launching device, the limitation on the lock key (4) is removed, the lock key (4) moves downwards under the action of the lock spring (8) to be in contact with the wedge limiting surface (21), the wedge (6) is limited to continue sliding leftwards, and the situation that the lock ring (14) is hindered to be lifted and the locking cannot be completed when the lock is locked next time is prevented.
8. An aircraft lock brake lock clearance relief arrangement according to claim 1, wherein: when the lock is locked, a lock ring (14) fixedly connected with the launching device collides with the lock hook (3), the lock hook (3) is driven to rotate anticlockwise around a lock hook rotating shaft (11), then a lock key (4) is upwards jacked to overcome a lock spring (8) and move upwards along a lock brake lock shell lug hole, after a lock hook supporting surface (29) is separated from a rocker arm supporting surface (28), a rocker arm (10) rotates anticlockwise to a locking position under the action of a parallel spring (9), the lock ring (14) continues to move upwards to a lock brake lock shell limiting surface (25) and then stops, a lock hook stopping surface (27) is attached to a rocker arm stopping surface (26), the lock hook (3) cannot rotate clockwise and is in a locking state, at the moment, a wedge block (6) slides leftwards along a built-in slide way (24) in the lock brake lock shell under the action of a wedge block spring (5), gaps are eliminated, and gapless locking is realized.
9. An aircraft lock brake lock clearance relief arrangement according to claim 1, wherein: when the lock is unlocked, a piston rod arranged in an unlocking actuator cylinder (2) pushes a shifting fork (7) to rotate anticlockwise around a shifting fork rotating shaft (12), the shifting fork (7) pushes a wedge block (6) to move rightwards along a slide way (24) arranged in a lock shell of a lock, a piston rod arranged in the unlocking actuator cylinder (2) continuously extends out, a rocker arm (10) is pushed to rotate clockwise along a rocker arm rotating shaft (15), a locking hook stop surface (27) is separated from a rocker arm stop surface (26), the rocker arm (10) pulls a locking hook (3) through a parallel spring (9), and the locking hook (3) rotates clockwise around a locking hook rotating shaft (11) to complete unlocking.
CN202120317075.8U 2021-02-03 2021-02-03 Locking clearance eliminating device for airplane locking device Active CN214493348U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202120317075.8U CN214493348U (en) 2021-02-03 2021-02-03 Locking clearance eliminating device for airplane locking device

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Application Number Priority Date Filing Date Title
CN202120317075.8U CN214493348U (en) 2021-02-03 2021-02-03 Locking clearance eliminating device for airplane locking device

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CN214493348U true CN214493348U (en) 2021-10-26

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CN202120317075.8U Active CN214493348U (en) 2021-02-03 2021-02-03 Locking clearance eliminating device for airplane locking device

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