Asynchronous backlash-free locking device

Abstract

The present invention discloses an asynchronous gapless locking device, which can automatically eliminate the locking gap and prevent the launch device from shaking. The present invention is realized by the following technical scheme: when locking, the lock ring fixedly connected to the launch device collides with the lock hook, driving the lock hook to rotate counterclockwise around the lock hook rotating shaft, pushing the lock key upward to overcome the key spring and move upward along the lock shell support ear hole. When the lock hook support surface is separated from the rocker arm support surface, the rocker arm rotates counterclockwise to the locking position under the action of the parallel spring, and the lock hook stop surface is in contact with the rocker arm stop surface, which is in a locked state. The wedge block slides to the left along the built-in slideway of the lock shell under the action of the wedge block spring to eliminate the gap and achieve gapless locking. When unlocking, the built-in piston rod of the unlocking actuator pushes the shift fork to rotate counterclockwise around the shift fork rotating shaft, the shift fork pushes the wedge block to move to the right, the piston rod extends, pushes the rocker arm to rotate clockwise, the lock hook stop surface is separated from the rocker arm stop surface, and the rocker arm pulls the lock hook through the parallel spring and rotates clockwise to complete the unlocking.

Description

Technical Field

[0001] The invention relates to an asynchronous gapless locking and unlocking device for an aircraft airborne system transmitting device. Background Art

[0002] The launcher is an important part of the aircraft's airborne system. When in use, the launcher is between the aircraft and the airborne vehicle. They form a complete airborne control system through mechanical, electrical and radio frequency connections. Whether the locking and unlocking of the launcher are reliable is directly related to the use of airborne launch and affects its launch efficiency. The interface between the launcher and the aircraft is usually called the launcher interface, including mechanical interface and electrical interface. At present, the commonly used mechanical connections on airborne launchers are bolt type, lifting ear and stop ear type, and fork ear type. Generally, a type of launcher has only one interface. Sometimes, in order to be suitable for different carriers, the launcher is required to have the ability to have multiple interfaces. The common method is to select an interface as the basic type, and add a transfer beam on the launcher when changing the interface. This "two-story" structure will increase the overall height and weight of the launcher a lot. The performance of the carrier will inevitably be reduced when it is installed and flying. With the continuous improvement of the requirements for electrical connections of airborne electronic products and the requirements for the outlet of the rear of airborne equipment, rear rectangular electrical connectors are widely used in airborne electronic equipment. The front locking device is one of the main structural parts of the airborne electronic equipment installed with the rear rectangular connector. The electronic equipment structure is usually composed of a chassis and a mounting frame. The two are generally formed into a whole through the front and rear tightening devices. The tightening device is composed of a lever latch combination handle (handle assembly) on the chassis and a fork-type positioning member (hook assembly) on the mounting frame. The handle assembly is fixed on the front panel of the chassis. When working, the push rod is released to place the chassis on the mounting frame, so that the lower end of the push rod contacts the pin shaft of the hook assembly fixed on the mounting frame, and then the push rod is pushed upward to lock it with the spring assembly. At this time, the chassis is locked; conversely, the spring sheet in the spring assembly is pushed to make the push rod bounce open to release the chassis lock. When the aircraft accelerates, the inertial force of the airborne aircraft acts on the rear stopper of the lock. At this time, it is necessary to prevent the rear stopper from lifting and causing the airborne aircraft to fall off from the back; when the aircraft decelerates, the inertial force of the airborne aircraft acts on the front stopper of the lock. At this time, it is necessary to prevent the front stopper from lifting and causing the airborne aircraft to fall off from the front. For conventionally designed locks, the unlocking force is about 2 times the weight of the aircraft, and the inertial force generated by the aircraft in various situations during takeoff and landing may exceed the unlocking force, especially when the aircraft landing cable blocks the forced deceleration, the aircraft will have an overload of more than 7. In order to ensure that the aircraft does not fall off the launch device under various circumstances, a set of mechanical safety mechanisms must be set on the lock. When the mechanism is in a locked state, in principle, even if the engine is ignited, the lock should constrain the aircraft on the launch device. Mechanical insurance can be classified into two categories in principle: electromagnetic mechanical insurance. It works on the DC power supply provided by the carrier. When it is not powered on, the mechanical insurance is in a locked state, and the lock provides a large locking force to the aircraft; after power is on, the mechanical insurance is opened, and the locking force is converted into a normal unlocking force. Inertial mechanical insurance.It uses an inertia hammer. When the aircraft is not overloaded, the mechanical safety controlled by the inertia hammer is in the open state, and the lock provides normal unlocking force. When the negative overload of the aircraft along the heading exceeds a certain value, the inertia hammer swings and the mechanical safety is in the locked state, thereby keeping the airborne aircraft on the launch device. The electromagnetic mechanical safety can ensure that as long as there is no launch command, no matter what state the carrier aircraft is in, the lock can restrain the airborne aircraft on the launch device, but the release of the electromagnetic mechanical safety depends on the power supply provided by the carrier aircraft. The inertial mechanical safety can adapt to the overload of the aircraft and ensure that the airborne aircraft will not fall off in various flight states, but its action is affected by the attitude of the carrier aircraft and the duration of the overload. The design is difficult and cannot meet the requirements of restraining the airborne aircraft on the launch device when the engine is accidentally ignited. There are two typical blocking structures of the lock: integrated blocking. The front and rear baffles are designed as a part that can rotate around two fulcrums. When loading and unloading an airborne aircraft, a wrench is used to rotate the baffle around the front fulcrum to lift the rear baffle and allow the airborne aircraft slider to enter between the baffles; when launching the airborne aircraft, the baffle rotates around the rear fulcrum to lift the front baffle and allow the airborne aircraft slider to pass smoothly. Separate baffle. The front and rear baffles are separated and can move independently. The front baffle rotates around a certain axis, while the rear baffle can use vertical movement or rotate around a certain axis at the back. The corresponding characteristics of the above two baffles are: integrated baffles. In order to prevent the airborne aircraft from falling off from the back of the launch device when the aircraft has a positive overload in the heading, after hanging the airborne aircraft, an air safety pin must be inserted to prevent the rear baffle from lifting when it is stressed. At the same time, the air safety pin must not hinder the baffle from rotating around the rear fulcrum. This structure will cause certain difficulties in the design of mechanical insurance. If the ignition contacts of the airborne aircraft engine are arranged on the lock, the use of this mechanism will cause the slide of the airborne aircraft to hit the ignition contacts during loading. There is a certain gap between the guide rail and the slider of the airborne aircraft in the up, down, left and right directions to ensure that there will be no obstruction during the de-orbit process. For sequential de-orbiting, the danger of the launch process mainly occurs when the airborne aircraft has only the last slider left. At this time, if the heading angle of the airborne aircraft relative to the launch device increases to the extent that the gap between the rear slider of the airborne aircraft and the guide rail is completely eaten up, bomb rack interference will occur. The electromagnetic mechanical insurance plays the same role on the ground and in the air, unlocking when powered on and locking when powered off. If the engine is accidentally ignited and stranded on the carrier aircraft, the consequence is that the tail of the carrier aircraft may be burned. In the air, since the suspension position of the airborne aircraft is a certain distance from the engine axis, it will also cause a side-slip torque to the aircraft, but the thrust of the airborne aircraft engine is much smaller than that of the aircraft engine, and the aircraft can still be controlled; on the ground, there may be ground crew, friendly aircraft, towers, villages, and people in front of the aircraft, and there may also be friendly aircraft in front of the air. If the airborne aircraft is allowed to detach from the launch device and launch, the harm caused is difficult to estimate.

[0003] As one of the important devices in the aircraft structure, the reliable locking and unlocking of the launcher directly affects the use of airborne weapons, so it is necessary to ensure sufficient rigidity. At present, the launchers of most models are manually locked and unlocked after being lifted into place by a motor. Since the motor cannot ensure that both ends of the launcher reach the locking position at the same time to complete the locking when lifting the launcher, the locking difficulty and the complexity of the lifting device are increased. Since the aircraft is subjected to a large aerodynamic load during flight, the locking device undergoes elastic deformation, and the difficulty of manual unlocking is increased after the gap is eliminated by the wedge block. In addition, under the condition of ensuring the rigidity requirements of the launcher lock ring, the existing locking device cannot meet the gapless locking requirements. Gapless locking means that there is no gap between the locked mechanism and the locking device after the locking device is locked, which can prevent the locked mechanism from shaking during the flight of the aircraft. Summary of the invention

[0004] The purpose of the present invention is to address the shortcomings of traditional locking methods of launchers and to propose a locking device suitable for asynchronous locking, capable of automatically eliminating locking gaps, preventing the launcher from shaking, integrating signal output, and using gas / hydraulic drive to unlock.

[0005] The technical solution adopted by the present invention to solve its technical problems is: an asynchronous gapless locking device, comprising: a lock shell 1 connected to the aircraft body by bolts, an unlocking actuator 2 connected to the upper front end of the lock shell 1 by axial fastening bolts 18 and a wedge 6 located below the unlocking actuator 2, a fork 7 fixedly connected to the bottom of the unlocking actuator 2 by a rotating shaft and connected to the actuating rod of the unlocking actuator 2 by a fork rotating shaft 12, a lock ring 14 fixedly connected to the launching device, a lock spring 8 fixedly connected to the ears on both sides of the lock shell 1 shell and passing through the ear holes to constrain the movement of the lock key 4 through the ears; a rocker arm 10 movably connected to the rocker arm rotating shaft 15 passing through the lock shell 1 box body, the rocker arm 10 extends out of the back end of the lock shell 1, and is connected to the lock hook 3 hooked on the lock ring 14 by the parallel spring 9 on the cantilever rotating shaft, and a lock hook rotating shaft 11 passing through the lock shell 1 box body, The wedge spring 5 connected to the spring fixing shaft on both sides of the lock shell 1 shell and the spring fixing shaft on the outer side of the wedge block 6 is fixedly connected to the travel switch 13 on the inner side of the lock shell 1 shell through the fastening bolts. When locking, the lock ring 14 fixedly connected to the launching device collides with the lock hook 3, driving the lock hook 3 to rotate counterclockwise around the lock hook rotating shaft 11, and then pushes the lock key 4 upward to overcome the lock spring 8 and move upward along the lock shell support ear hole. When the lock hook support surface 29 is disengaged from the rocker arm support surface 28, the rocker arm 10 rotates counterclockwise to the locked position under the action of the parallel spring 9, and the lock ring 14 continues to move upward to the lock shell limit surface 25 and then stops. The lock hook stop surface 27 is in contact with the rocker arm stop surface 26, and the lock hook 3 cannot rotate clockwise and is in a locked state. At this time, the wedge 6 slides to the left along the built-in slideway 24 of the lock shell under the action of the wedge spring 5 to eliminate the gap and achieve gapless locking. When unlocking, air / hydraulic pressure is supplied to the unlocking actuator 2 which is provided with the unlocking nozzle 16, and the built-in piston rod of the unlocking actuator 2 pushes the shift fork 7 to rotate counterclockwise around the shift fork shaft 12, and the shift fork 7 pushes the wedge block 6 to move rightward along the built-in slideway 24 of the lock housing, and then the built-in piston rod of the unlocking actuator 2 continues to extend, and then pushes the rocker arm 10 to rotate clockwise along the rocker arm shaft 15, and when the lock hook stop surface 27 is disengaged from the rocker arm stop surface 26, the rocker arm 10 pulls the lock hook 3 through the parallel spring 9, and the lock hook 3 rotates clockwise around the lock hook shaft 11 to complete the unlocking.

[0006] Compared with the prior art, the present invention has the following beneficial effects:

[0007] The present invention adopts an automatic gap elimination mechanism, which automatically eliminates the gap between the lock ring and the limit surface of the lock shell after locking, prevents the launch device from shaking during the flight of the aircraft, and realizes gapless locking. Combined with the height difference between the lock ring and the limit surface of the lock shell after locking, the lock hook can continue to rotate upward by a certain angle after having the locking ability, thereby realizing asynchronous locking of the airborne launch device; an integrated signal output device is used to output a locked-in position signal after locking; when the launch device is lowered, gas / hydraulic pressure is used to realize rapid unlocking, thereby improving the reliability, safety and maintainability of the launch device. BRIEF DESCRIPTION OF THE DRAWINGS

[0008] Figure 1 It is a structural schematic diagram of the asynchronous gapless locking device of the present invention.

[0009] Figure 2 yes Figure 1 Schematic diagram of unlocking status.

[0010] Figure 3 yes Figure 1 Schematic diagram of the locked state.

[0011] Figure 4 yes Figure 1 Schematic diagram of the gap elimination mechanism.

[0012] Figure 5 yes Figure 1 Schematic diagram of the left and right end locking ring positions.

[0013] Figure 6 yes Figure 1 Schematic diagram of the lock housing on one side.

[0014] In the figure: 1 lock housing, 2 unlocking actuator, 3 lock hook, 4 lock key, 5 wedge spring, 6 wedge, 7 fork, 8 lock spring, 9 parallel spring, 10 rocker arm, 11 lock hook shaft, 12 fork shaft, 13 signal output device, 14 lock ring, 15 rocker arm shaft, 16 unlocking nozzle, 17 bolt shaft, 18 fastening bolt, 19 wedge front inclined surface, 20 wedge rear inclined surface, 21 wedge limiting surface, 22 left end lock ring, 23 right end lock ring, 24 lock housing built-in slide, 25 lock housing limiting surface, 26 rocker arm stop surface, 27 lock hook stop surface, 28 rocker arm support surface, 29 lock hook support surface. DETAILED DESCRIPTION

[0015] See also Figure 1-Figure 5In the embodiment described below, an asynchronous gapless locking device comprises: a lock housing 1 connected to an aircraft body by bolts, an unlocking actuator 2 connected to the upper front end of the lock housing 1 by an axial fastening bolt 18, and a wedge 6 located below the unlocking actuator 2, a fork 7 fixedly connected to the bottom of the unlocking actuator 2 by a rotating shaft and connected to the actuating rod of the unlocking actuator 2 by a fork rotating shaft 12, a lock ring 14 fixedly connected to a launching device, a lock spring 8 fixedly connected to the ears on both sides of the lock housing 1 and passing through the ear holes to restrict the movement of the lock key 4 by the ears; a rocker arm 10 movably connected to a rocker arm rotating shaft 15 passing through the lock housing 1 body, the rocker arm 10 extending out of the back end of the lock housing 1, connected to a lock hook 3 hooked to the lock ring 14 by a parallel spring 9 on the cantilever rotating shaft, a lock hook rotating shaft 11 passing through the lock housing 1 body, and connected to the lock housing 1 The wedge springs 5 ​​of the spring fixing axes on both sides of the shell and the spring fixing axes on the outer sides of the wedge block 6 are fixedly connected to the travel switch 13 on the inner side of the lock shell 1 shell through the fastening bolts. When locking, the lock ring 14 fixedly connected to the launching device collides with the lock hook 3, driving the lock hook 3 to rotate counterclockwise around the lock hook rotating shaft 11, and then pushes the lock key 4 upward to overcome the lock spring 8 and move upward along the lock shell ear hole. When the lock hook support surface 29 is disengaged from the rocker arm support surface 28, the rocker arm 10 rotates counterclockwise to the locked position under the action of the parallel spring 9, and the lock ring 14 continues to move upward to the lock shell limit surface 25 and then stops. The lock hook stop surface 27 is in contact with the rocker arm stop surface 26, and the lock hook 3 cannot rotate clockwise and is in a locked state. At this time, the wedge 6 slides to the left along the built-in slideway 24 of the lock shell under the action of the wedge spring 5 to eliminate the gap and achieve gapless locking. When unlocking, air / hydraulic pressure is supplied to the unlocking actuator 2 provided with the unlocking nozzle 16, and the built-in piston rod of the unlocking actuator 2 pushes the shift fork 7 to rotate counterclockwise around the shift fork shaft 12, and the shift fork 7 pushes the wedge block 6 to move rightward along the built-in slideway 24 of the lock housing, and then the built-in piston rod of the unlocking actuator 2 continues to extend, pushing the rocker arm 10 to rotate clockwise along the rocker arm shaft 15, and when the lock hook stop surface 27 is disengaged from the rocker arm stop surface 26, the rocker arm 10 pulls the lock hook 3 through the parallel spring 9, and the lock hook 3 rotates clockwise around the lock hook shaft 11 to complete the unlocking.

[0016] See also Figure 2. Unlocking process: When the launch device is lowered from the aircraft's bomb bay, the locking device unlocking action must be completed first. Supply air / hydraulic pressure to the unlocking actuator 2 equipped with an unlocking nozzle 16. The air / hydraulic pressure enters the unlocking actuator 2 through the unlocking nozzle 16. The built-in piston rod of the unlocking actuator 2 first pushes the bolt shaft 17 to push the fork 7 to rotate counterclockwise around the fork shaft 12. The fork 7 pushes the wedge block 6 to slide to the right along the built-in slide 24 of the lock housing. Then the built-in piston rod of the unlocking actuator 2 continues to push the rocker arm 10 to rotate clockwise around the rocker arm shaft 15. When the rocker arm 10 is rotated to disengage from the stop surface of the lock hook 3, the lock hook 3 rotates clockwise around the lock hook shaft 11 under the action of the parallel spring 9 and the gravity of the launch device. When the lock hook 3 rotates a certain angle, The lock ring 14 slides out of the lock hook 3, and the launching device completes the lowering action under the action of the lifting motor. After the pressure supply to the unlocking nozzle 16 stops, the unlocking actuator 2 completes the retraction action under the action of its built-in spring, and pulls back the shift fork 7 at the same time, releasing the restriction on the wedge block 6. The wedge block 6 will slide to the left along the lock shell 1 with a slideway under the action of the wedge block spring 5. When it slides to the position of the lock key 4, the wedge block limit surface 21 is restricted by the lock key 4 and cannot continue to slide to the left, thereby not affecting the next time the lock ring 14 hits the lock hook 3 to complete the locking action, and the entire unlocking process is completed.

[0017] See also Figure 3. One such locking device is arranged on each side of the bomb bay of the aircraft. The lifting of the launch device is completed by a set of lifting motors, and the locking device completes the locking after the lifting is in place. The locking process is described below by taking the left end of the launch device lifted into place first as an example: when the launch device is lifted from the ground to the bomb bay of the aircraft, as the launch device is lifted, the left end of the launch device is in place first, and the left end locking ring 22 fixed to the launch device first collides with the lock hook 3 of the left end locking device, and drives the lock hook 3 to rotate counterclockwise around the lock hook rotating shaft 11. When it rotates until the lock hook support surface 29 is separated from the rocker arm support surface 28, the rocker arm 10 rotates counterclockwise to the locked position under the action of the parallel spring 9, and the rocker arm 10 triggers the signal output device to output a locking signal. At this time, the left end locking device has the locking ability. As the launch device continues to be lifted upward, the left end locking ring 22 pushes the lock key 4 to overcome the lock spring 8 and move upward. When the lock key 4 moves upward to be separated from the wedge block limit surface 21, the wedge block 6 is driven by the wedge block spring 5. With the movement from bottom to left, the front inclined surface 19 of the wedge block contacts the left end locking ring 22 and then slides in the opposite direction to the right. As the left end locking ring 22 continues to move upward, the right end locking ring 23 has completed the right end locking in the same steps. After the left end locking ring 22 moves to the lock shell limiting surface 25, the left end locking ring 22 is limited by the lock shell 1 and cannot continue to move upward. At this time, the lifting motor stops lifting (the right end locking ring 23 does not need to move to the lock shell 1, and has the locking ability). Then the lifting motor is reversed, and the launching device with the locking ring 14 is lowered, driving the locking hook 3 to rotate clockwise around the locking hook shaft 11. When the stop surface of the locking hook 3 contacts the stop surface of the rocker arm 10, the locking hook 3 cannot continue to rotate clockwise around the locking hook shaft 11, and the locking ring 14 is hooked by the locking hook 3 and cannot continue to be lowered. The lifting motor stops working, completing the entire locking process.

[0018] See also Figure 4 The gap elimination mechanism mainly includes a lock key 4 equipped with a lock spring 8, a wedge 6 hung with a wedge spring 5, a wedge limit surface 21 with a sunken step formed at the front end of the wedge 6, and a wedge front inclined surface 19 and a wedge rear inclined surface 20 located below the wedge limit surface 21 formed on the wedge 6. The wedge angle of the wedge front inclined surface 19 is greater than the arctan function arctanμ, and the wedge angle of the wedge rear inclined surface 20 is less than the arctan function arctanμ, where μ is the friction coefficient between the wedge 6 and the lock housing limit surface 25. After locking, when there is a gap between the lock ring 14 and the lock housing limit surface 25, the wedge 6 automatically slides to the left under the action of the wedge spring 5, and the gap is eliminated by the wedge rear inclined surface 20. After unlocking, the lock ring 14 is lowered with the launching device, releasing the restriction on the lock key 4. The lock key 4 moves downward under the action of the lock spring 8 until it contacts the wedge block limit surface 21, restricting the wedge block 6 from continuing to slide to the left, preventing the lock ring 14 from being hindered from lifting when locking next time, thereby failing to complete the locking.

[0019] The above is a preferred embodiment of the present invention. It should be noted that the above embodiment is for illustration of the present invention, but the present invention is not limited thereto, and those skilled in the art may design alternative embodiments without departing from the scope of the appended claims. For those of ordinary skill in the art, various modifications and improvements may be made without departing from the spirit and essence of the present invention, and these modifications and improvements are also considered to be within the scope of protection of the present invention.

Claims

1. An asynchronous gapless locking device, comprising: The clearance elimination mechanism comprises a lock key (4) equipped with a lock spring (8), a wedge (6) hung with a wedge spring (5); and further comprises: a lock housing (1) connected to an aircraft body by bolts, an unlocking actuator (2) connected to the upper front end of the lock housing (1) by axial fastening bolts (18), and a wedge (6) located below the unlocking actuator (2), fixedly connected to the bottom of the unlocking actuator (2) by a rotating shaft, and connected to the unlocking actuator (2) by a shift fork rotating shaft (12). A shift fork (7) connected to a moving rod, a lock ring (14) fixedly connected to a launching device, a lock spring (8) fixedly connected to ears on both sides of a lock housing (1) and passing through ears, and constraining the movement of a lock key (4) through ears; a rocker arm (10) movably connected to a rocker arm rotating shaft (15) passing through a housing of the lock housing (1), the rocker arm (10) extending out of the back end of the lock housing (1), connected to a lock hook (3) hooked to the lock ring (14) through a parallel spring (9) on a cantilever rotating shaft, and passing through a lock hook rotating shaft (15) of the housing of the lock housing (1) to form a lock hook (3) hooked to the lock ring (14). 11), a wedge spring (5) connecting the spring fixing shafts on both sides of the lock housing (1) and the spring fixing shafts on the outer side of the wedge (6), and a travel switch (13) fixedly connected to the inner side of the lock housing (1) through a fastening bolt, characterized in that: when locking, a lock ring (14) fixedly connected to the launching device collides with the lock hook (3), driving the lock hook (3) to rotate counterclockwise around the lock hook rotating shaft (11), and then pushing the lock key (4) upward to overcome the lock spring (8) and move upward along the lock housing support ear hole, when the lock hook support surface ( After the locking hook (29) is separated from the rocker arm support surface (28), the rocker arm (10) rotates counterclockwise to the locked position under the action of the parallel spring (9), and the lock ring (14) continues to move upward to the lock housing limit surface (25) and then stops. The lock hook stop surface (27) is in contact with the rocker arm stop surface (26), and the lock hook (3) cannot rotate clockwise and is in a locked state. At this time, the wedge block (6) slides to the left along the built-in slideway (24) of the lock housing under the action of the wedge block spring (5), eliminating the gap and realizing gapless locking; When unlocking, air / hydraulic pressure is supplied to the unlocking actuator (2) provided with the unlocking nozzle (16), and the piston rod built into the unlocking actuator (2) pushes the shift fork (7) to rotate counterclockwise around the shift fork rotating shaft (12), and the shift fork (7) pushes the wedge block (6) to move rightward along the built-in slideway (24) of the lock housing, and then the piston rod built into the unlocking actuator (2) continues to extend, and then pushes the rocker arm (10) to rotate clockwise along the rocker arm rotating shaft (15), and when the lock hook stop surface (27) is separated from the rocker arm stop surface (26), the rocker arm (10) pulls the lock hook (3) through the parallel spring (9), and the lock hook (3) rotates clockwise around the lock hook rotating shaft (11), completing the unlocking; The gas / hydraulic pressure enters the unlocking actuator (2) through the unlocking nozzle (16). The piston rod built into the unlocking actuator (2) first pushes the bolt shaft (17), driving the shift fork (7) to rotate counterclockwise around the shift fork shaft (12). The shift fork (7) pushes the wedge block (6) to slide rightward along the built-in slideway (24) of the lock housing. The piston rod built into the unlocking actuator continues to push the rocker arm (10) to rotate clockwise around the rocker arm shaft (15) until the rocker arm (10) is separated from the stop surface of the lock hook (3). The lock hook (3) rotates clockwise around the lock hook shaft (11) under the action of the parallel spring (9) and the gravity of the launching device. When the lock hook (3) rotates a certain angle, After that, the lock ring (14) slides out of the lock hook (3), and the launching device completes the lowering action under the action of the lifting motor. After the pressure supply to the unlocking nozzle (16) stops, the unlocking actuator (2) completes the retraction action under the action of its built-in spring, and at the same time pulls back the shift fork (7), releasing the restriction on the wedge block (6). Under the action of the wedge block spring (5), the wedge block (6) slides to the left along the lock housing (1) with a slideway and slides to the position of the lock key (4). The wedge block limit surface (21) is restricted by the lock key (4) and cannot continue to slide to the left, so as not to affect the next time the lock ring (14) hits the lock hook (3) to complete the locking action, and the entire unlocking process is completed.

2. The asynchronous gapless locking device according to claim 1, characterized in that: After the left end of the launch device is in place first, the left end lock ring (22) fixedly connected to the launch device first collides with the lock hook (3) of the left end locking device, and drives the lock hook (3) to rotate counterclockwise around the lock hook rotating shaft (11). After the lock hook support surface (29) is disengaged from the rocker arm support surface (28), the rocker arm (10) rotates counterclockwise to the locking position under the action of the parallel spring (9), and the rocker arm (10) triggers the signal output device to output a locking signal, and the left end locking device has the locking capability.

3. The asynchronous gapless locking device according to claim 1, characterized in that: The launching device is lifted upward, and the left end locking ring (22) pushes the locking key (4) to overcome the locking spring (8) and move upward. After the locking key (4) moves upward until it is separated from the wedge block limiting surface (21), the wedge block (6) moves to the left under the action of the wedge block spring (5), and the front inclined surface (19) of the wedge block contacts the left end locking ring (22) and then slides to the right in the opposite direction.

4. The asynchronous gapless locking device according to claim 2, characterized in that: The left end locking ring (22) moves upward, and the right end locking ring (23) has completed the right end locking in the same steps. After the left end locking ring (22) moves to the lock shell limiting surface (25), the left end locking ring (22) is limited by the lock shell (1) and cannot continue to move upward. At this time, the lifting motor stops lifting, and the right end locking ring (23) does not need to move to the lock shell (1) and has the locking ability.

5. The asynchronous gapless locking device according to claim 3, characterized in that: The lifting motor is reversed, and the launching device with the lock ring (14) is lowered, driving the lock hook (3) to rotate clockwise around the lock hook rotating shaft (11). The stop surface of the lock hook (3) contacts the stop surface of the rocker arm (10), and the lock hook (3) cannot continue to rotate clockwise around the lock hook rotating shaft (11). The lock ring (14) is hooked by the lock hook (3) and cannot continue to be lowered. The lifting motor stops working, and the whole locking process is completed.

6. The asynchronous gapless locking device according to claim 1, characterized in that: The front end of the wedge block (6) is provided with a wedge block limiting surface (21) with a sunken step, and the wedge block (6) is also provided with a wedge block front inclined surface (19) and a wedge block rear inclined surface (20) located below the wedge block limiting surface (21), the wedge angle of the wedge block front inclined surface (19) is greater than the inverse tangent function arctanμ, and the wedge angle of the wedge block rear inclined surface (20) is less than the inverse tangent function arctanμ, wherein μ is the friction coefficient between the wedge block (6) and the lock housing limiting surface (25).

7. The asynchronous gapless locking device according to claim 6, characterized in that: After locking, when there is a gap between the lock ring (14) and the lock housing limit surface (25), the wedge (6) automatically slides to the left under the action of the wedge spring (5), and the gap is eliminated by the wedge rear inclined surface (20).

8. The asynchronous gapless locking device according to claim 6, characterized in that: After unlocking, the lock ring (14) is lowered along with the launching device, releasing the restriction on the lock key (4). The lock key (4) moves downward under the action of the lock spring (8) until it contacts the wedge block limit surface (21), restricting the wedge block (6) from sliding further to the left, thereby preventing the lock ring (14) from being hindered from lifting when locking next time, thereby preventing the lock from being completed.

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