An automatically resettable gravity release latching mechanism for drop test

Abstract

The application provides an automatic reset gravity release locking mechanism for a drop test, and belongs to the technical field of airplane drop tests, and comprises a lock body main outer plate, a lock jaw, a lock tongue, an electric permanent magnet assembly, a locking block, a fixed guide rail and a main shaft pin, the top end of the lock body main outer plate is connected with a hydraulic lifting cylinder, the electric permanent magnet assembly is located on the upper side of the fixed guide rail, the locking block is sleeved and fixed on a top rod, the side surface of the locking block is matched with the fixed guide rail, one end of the top rod penetrates through the electric permanent magnet assembly, and the other end is provided with the lock tongue on the lower side, the lateral side surfaces of the locking block are connected with the upper end of the lock jaw through a locking connecting rod, the middle part of the lock jaw is fixed on the lock body main outer plate through the main shaft pin, and the lower end of the lock jaw clamps the lock tongue; in the locking state, the locking block is connected with the electric permanent magnet assembly under the action of magnetic force, and the connecting point position of the locking connecting rod and the locking block is lower than the connecting point position of the locking connecting rod and the lock jaw. The scheme has short unlocking response time, low maintenance cost, and improves the full-airplane repeated drop test efficiency and safety margin.

Description

Technical Field

[0001] This application relates to the field of aircraft drop test technology, and in particular to an automatically reset gravity release locking mechanism for drop tests. Background Technology

[0002] Full-aircraft drop tests are a core technical means to verify the impact resistance of aircraft structures. By simulating the impact loads during carrier landings, the reliability of the airframe structure, landing gear, and onboard equipment is assessed. During a full-aircraft drop test, the entire aircraft is raised to a predetermined height and released within milliseconds, allowing it to fall freely onto the test platform, replicating the landing conditions on an aircraft carrier deck. The lift-lock release mechanism is a critical piece of equipment in the full-aircraft drop test, and its performance directly affects the safety and reliability of the test. Furthermore, in repeated drop tests, whether it can automatically engage after deployment directly affects the test efficiency and progress. Technically, existing lift-lock release mechanisms are mostly divided into three types: manual release hooks with earth-tamping hammers, electromagnetic release locks, and hydraulic ball-type release locks. Manual release hooks require manual locking and unlocking, which does not meet the requirements for locking at heights and safe remote release. Electromagnetic release locks lose their locking ability upon power failure, and hydraulic release locks have long release times, failing to meet the millisecond-level release requirements of aircraft. In terms of cost and efficiency, due to the limitations of the aircraft's drop attitude, it is difficult to ensure the alignment of the locking tongue and the locking device after deployment, which increases the difficulty of automatic locking. Traditional release locks cannot automatically lock, and after each deployment, the installation personnel need to perform a secondary locking of the lifting locking device, which increases work efficiency. Traditional mechanical gripper release locks are prone to wear with the test piece and have poor impact resistance. Repeated drop tests can easily lead to damage to the locking device, increasing costs. Summary of the Invention

[0003] In view of this, the present application provides an automatically reset gravity release locking mechanism for drop tests, which at least partially solves the problems of stability and reliability of large-tonnage release locks, automatic locking of the locking mechanism after deployment, and millisecond-level deployment of locking equipment for drop tests of carrier-based aircraft in the prior art.

[0004] This application provides an automatic reset gravity release locking mechanism for drop testing, including a main outer plate of the lock body, a locking claw, and a locking tongue. It also includes an electro-permanent magnet assembly, a locking block, a fixed guide rail, and a main shaft pin fixed to the main outer plate of the lock body. The top of the main outer plate of the lock body connects the entire release locking mechanism to a hydraulic lifting actuator via a first connector. The electro-permanent magnet assembly is located on the upper side of the fixed guide rail. The locking block is sleeved and fixed on a top rod, with the side of the locking block facing the main outer plate of the lock body engaging with the fixed guide rail. One end of the top rod passes through the electro-permanent magnet assembly, and a locking tongue is provided on the lower side of the other end of the top rod. The two lateral sides of the locking block are connected to the upper ends of the locking claws via locking connecting rods. The middle part of the locking claw is fixed to the main outer plate of the lock body via a main shaft pin, and the lower end of the locking claw clamps the locking tongue. In the locked state, the locking block connects to the electro-permanent magnet assembly under magnetic force. The connection point between the locking connecting rod and the locking block is lower than the connection point between the locking connecting rod and the locking claw.

[0005] According to a specific implementation of an embodiment of this application, the locking block includes a locking block body and a locking block pin. The center of the locking block body is provided with a first through hole along the direction of the release locking mechanism. The locking block body is sleeved on the top rod through the first through hole. The side of the locking block body is provided with an opening groove along the direction of the release locking mechanism. The locking block pin passes vertically through the two side walls of the opening groove. One end of the locking connecting rod is connected to the locking block pin located in the opening groove, and the other end of the locking connecting rod is connected to the upper end of the locking claw.

[0006] According to a specific implementation of an embodiment of this application, the locking block further includes a bushing. The side of the locking block body facing the main outer plate of the lock body has a groove. The groove cooperates with the fixed guide rail. The bushing is fixed in the groove. The bushing is used to reduce wear and vibration when the locking block moves vertically along the fixed guide rail.

[0007] According to a specific implementation of an embodiment of this application, the push rod includes a main push rod and a thin push rod. The locking block is sleeved on the thin push rod. The thin push rod passes through the top end of the electro-permanent magnet assembly and is provided with a limiting block. An energy storage component is sleeved on the thin push rod between the locking block and the electro-permanent magnet assembly. The energy storage component is used to quickly release energy when a release command is triggered, drive the main push rod to move downward, and drive the locking link to move beyond the mechanical dead point, thereby realizing rapid unlocking and release.

[0008] According to a specific implementation of an embodiment of this application, the top rod further includes a connecting flange, which is fixedly sleeved on the main top rod, and the bottom of the locking block is fixedly connected to the top rod through the connecting flange.

[0009] According to one specific implementation of the embodiments of this application, the energy storage component is configured as an energy storage spring.

[0010] According to a specific implementation of the present application, the locking claw is configured as a symmetrical clamp-shaped lever structure, and the lower jaw of the clamp-shaped lever structure is provided with a bearing plane that matches the locking tongue.

[0011] According to a specific implementation of the present application, the top of the lock tongue is designed with a mushroom head. During the locking phase, the mushroom head cooperates with the bearing plane of the lock claw. During the unlocking and releasing phase, the mushroom head automatically opens the lock claw to achieve gravity unlocking.

[0012] According to a specific implementation of the present application, the fixed guide rail is configured as a convex-shaped structure, and the protruding part of the convex-shaped structure is located in the middle of the electro-permanent magnet assembly; a plurality of countersunk holes are evenly arranged vertically in the middle part of the convex-shaped structure, and the main outer plate of the lock body is connected by bolts inserted into the countersunk holes.

[0013] According to a specific implementation of an embodiment of this application, the main outer plate of the lock body is configured as a double-sided clamping plate structure, and each side of the main outer plate of the lock body is provided with a fixed guide rail.

[0014] Beneficial effects:

[0015] The automatically reset gravity-release locking mechanism for drop tests in this embodiment employs a near-dead-point locking mechanism, which can provide a locking force far greater than the external load under relatively small electromagnetic force. This ensures the stability and reliability of the locking state of large-tonnage aircraft during drop tests, effectively preventing accidental unlocking due to environmental vibration disturbances and meeting the high safety margin requirements of drop tests. Simultaneously, the electromagnetic triggering method results in a short unlocking response time, achieving millisecond-level release, effectively meeting the technical requirements of synchronous unlocking time and repeated release accuracy in repeated drop tests of the entire aircraft. Furthermore, it features an automatic reset function, autonomously restoring to the initial locked state after each drop test, eliminating the need for manual climbing for secondary locking operations. This significantly improves the efficiency of repeated drop tests of the entire aircraft and effectively reduces the risks of high-altitude operations and manual maintenance costs. Attached Figure Description

[0016] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 This is a schematic diagram of the external appearance of an automatically resettable gravity release locking mechanism for drop testing according to an embodiment of the present invention; Figure 2 This is a structural diagram of an automatically resettable gravity release locking mechanism for drop testing according to an embodiment of the present invention; Figure 3 This is a schematic diagram of a fixed guide rail according to an embodiment of the present invention; Figure 4This is a schematic diagram of the assembly of the locking block and the push rod according to an embodiment of the present invention; Figure 5 This is a schematic diagram of the assembly of the locking block and the push rod according to an embodiment of the present invention from another angle; Figure 6 This is a diagram of a push rod structure according to an embodiment of the present invention; Figure 7 This is a schematic diagram of electromagnetic force calculation according to an embodiment of the present invention; Figure 8 The diagram shows the locking and unlocking states of an automatically reset gravity release locking mechanism for drop testing according to an embodiment of the present invention. (a) shows the locking state, and (b) shows the unlocking state.

[0018] In the diagram: 0. Hydraulic lifting actuator cylinder; 1. Hydraulic cylinder connecting pin; 2. Lock body main outer plate; 3. Electro-permanent magnet assembly; 4. Locking block; 41. Locking block body; 42. Locking block pin; 43. Bushing; 5. Top rod; 51. Limit block; 52. Energy storage spring; 53. Connecting flange; 54. Main top rod; 6. Fixed guide rail; 7. Locking connecting rod; 8. Main shaft pin; 9. Locking claw; 10. Locking tongue. Detailed Implementation

[0019] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0020] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. This application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be noted that, in the absence of conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0021] It should be noted that various aspects of embodiments within the scope of the appended claims are described below. It will be apparent that the aspects described herein can be embodied in a wide variety of forms, and any particular structure and / or function described herein is merely illustrative. Based on this application, those skilled in the art will understand that one aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects set forth herein can be used to implement the device and / or practice the method. Additionally, this device and / or method can be implemented using structures and / or functionalities other than one or more of the aspects set forth herein.

[0022] It should also be noted that the illustrations provided in the following embodiments are only schematic representations of the basic concept of this application. The illustrations only show the components related to this application and are not drawn according to the number, shape and size of the components in actual implementation. In actual implementation, the form, quantity and proportion of each component can be arbitrarily changed, and the layout of the components may also be more complex.

[0023] Furthermore, specific details are provided in the following description to facilitate a thorough understanding of the examples. However, those skilled in the art will understand that the described aspects can be practiced without these specific details.

[0024] In one embodiment, an automatically resettable gravity-release locking mechanism for drop testing is provided, referring to... Figure 1 and Figure 2 The lock body includes a main outer plate 2, a locking claw 9, and a locking tongue 10. It also includes an electro-permanent magnet assembly 3, a locking block 4, a fixed guide rail 6, and a main shaft pin 8 fixed to the main outer plate 2. The top of the main outer plate 2 connects the entire release locking mechanism to the hydraulic lifting actuator 0 via a first connector. The electro-permanent magnet assembly 3 is located on the upper side of the fixed guide rail 6. The locking block 4 is sleeved and fixed on the top rod 5. The side of the locking block 4 facing the main outer plate 2 cooperates with the fixed guide rail 6. The top rod 5... One end passes through the electro-permanent magnet assembly 3, and the lower side of the other end of the top rod 5 is provided with a locking tongue 10. The two sides of the locking block 4 are connected to the upper end of the locking claw 9 through the locking connecting rod 7. The middle part of the locking claw 9 is fixed to the main outer plate 2 of the lock body through the main shaft pin 8. The lower end of the locking claw 9 clamps the locking tongue 10. In the locking state, the locking block 4 is connected to the electro-permanent magnet assembly 3 under the action of magnetic force. The position of the connection point between the locking connecting rod 7 and the locking block 4 is lower than the position of the connection point between the locking connecting rod 7 and the locking claw 9.

[0025] In specific implementation, the first connecting component is set as a hydraulic cylinder connecting pin 1. The hydraulic cylinder connecting pin 1 is used to connect the entire release locking mechanism to the upper hydraulic lifting actuator cylinder 0. The hydraulic cylinder connecting pin 1 needs to bear the weight of the lock body and the entire load of the large-tonnage suspended object at the lower end, and must be made of high-strength alloy steel to resist shear stress. The main outer plate 2 of the lock body, as the core load-bearing skeleton of the device, adopts a double-sided clamping plate structure design, which can provide precise installation and positioning holes for the internal electro-permanent magnet assembly 3, locking block 4, fixed guide rail 6 and main shaft pin 8, and can also smoothly transmit the lower tension during the load-bearing process to prevent the mechanism from deforming under stress.

[0026] The electro-permanent magnet assembly 3, serving as the main unlocking structure of the device, is installed above the fixed guide rail 6. The electro-permanent magnet assembly 3 maintains its magnetic force when power is off and demagnetizes instantly when power is applied. When the system is in a dead-point locking state, the electro-permanent magnet assembly 3 adheres to the top of the locking block 4, providing additional mechanical locking force. This prevents accidental damage to the dead point due to vibrations or other conditions at the test site, ensuring safety during heavy-load suspension. When unlocking is required, demagnetization upon power application instantly releases the safety mechanism without affecting the response speed of gravity release, ensuring that the locking tongue 10 releases within milliseconds.

[0027] In one embodiment, refer to Figure 4 and Figure 5 The locking block 4 includes a locking block body 41 and a locking block pin 42. The center of the locking block body 41 is provided with a first through hole along the direction of the release locking mechanism. The locking block body 41 is sleeved on the top rod 5 through the first through hole. The side of the locking block body 41 is provided with an opening groove along the direction of the release locking mechanism. The locking block pin 42 passes vertically through the two side walls of the opening groove. One end of the locking connecting rod 7 is connected to the locking block pin 42 located in the opening groove, and the other end of the locking connecting rod 7 is connected to the upper end of the locking claw 9.

[0028] Furthermore, the locking block 4 also includes a bushing 43. The side of the locking block body 41 facing the main outer plate 2 of the lock body has a groove. The groove cooperates with the fixed guide rail 6. The bushing 43 is fixed in the groove. The bushing 43 is used to reduce the wear and vibration of the locking block 4 when it moves vertically along the fixed guide rail 6.

[0029] In specific implementation, the locking block 4 is set as a slider structure rigidly fixed to the middle section of the top rod 5, used to connect the locking link 7 below. In the locked state, the locking block 4 is connected to the electro-permanent magnet assembly 3 under the action of magnetic force. After release, it falls freely along the fixed guide rail 6. In the reset stage, it rises along the fixed guide rail 6 under the pushing force of the top rod 5 until it contacts the electro-permanent magnet assembly 3. At this time, it is magnetized, and the entire release locking mechanism returns to the locked state. The function of the locking block body 41 is to drive the locking link 7 through the locking block shaft pin 42 under the pushing force of the top rod 5, thereby completing the closing of the locking claw 9 and realizing the automatic locking function. The function of the locking block shaft pin 42 is to connect the locking block body 41 and the locking link 7.

[0030] In one embodiment, refer to Figure 6 The push rod 5 includes a main push rod 54 and a thin push rod. The locking block 4 is sleeved on the thin push rod. The thin push rod passes through the top end of the electro-permanent magnet assembly 3 and is provided with a limiting block 51. An energy storage component is sleeved on the thin push rod between the locking block 4 and the electro-permanent magnet assembly 3. The energy storage component is used to quickly release energy when a release command is triggered, drive the main push rod 54 to move downward, and drive the locking link 7 to move beyond the mechanical dead point, so as to realize rapid unlocking and release.

[0031] Furthermore, the push rod 5 also includes a connecting flange 53, which is fixedly sleeved on the main push rod 54. The bottom of the locking block 4 is fixedly connected to the push rod 5 through the connecting flange 53. Specifically, the locking block 4 is connected to the connecting flange 53 of the push rod 5 through the bolt hole at its bottom.

[0032] Furthermore, the energy storage component is configured as an energy storage spring 52.

[0033] In practical implementation, the push rod 5 pushes the locking block 4, ensuring that the locking block 4 can return to its initial position after unlocking and automatically re-engage, while also serving as a limit switch. The fixed guide rail 6 is fastened to the inner side of the main outer plate 2 of the lock body by bolts, providing high-precision linear guidance for the lifting and lowering of the locking block 4 and the push rod 5, thereby effectively eliminating the risk of lateral displacement and jamming of the push rod 5 during force-driven movement, ensuring smooth operation and repeatability of the mechanism.

[0034] The main function of the limiting block 51 is to limit the compression stroke of the energy storage spring 52. The energy storage spring 52 is coaxially sleeved on the upper half of the push rod 5 (the thin push rod). Its core function is to store some elastic potential energy. When the release command is triggered, the energy storage spring 52 quickly releases energy, driving the main push rod 54 to move downward to assist the lower locking link 7 in overcoming the mechanical dead point, thereby ensuring the rapid unlocking and release of the release lock. In addition, during the reset phase, it can also prevent the locking block 4 from hard collision with the electro-permanent magnet assembly 3, playing a certain buffering role. The connecting flange 53 is responsible for connecting the push rod 5 and the locking block 4, ensuring that the locking block 4 can move vertically under the action of the push rod 5. The main function of the main push rod 54 is to correctly transmit the upward thrust of the lock tongue 10 to the locking block 4 during the automatic reset phase, thereby causing the locking link 7 to drive the lock claw 9 to close, achieving the purpose of automatic reset locking.

[0035] Furthermore, the locking linkages 7 are symmetrically distributed, with their inner ends connected to the locking block 4 via the locking block pin 42, and their outer ends connected to the upper lever arm of the locking claw 9 via pins. In the locked state, the push rod 5 pushes the two locking linkages 7 outward to a near-horizontal centerline (i.e., the mechanical dead point). At this time, the downward pulling force of the weight below is converted into the internal force of the linkage expanding outward, making the mechanism tighter and tighter, thereby achieving dead point self-locking.

[0036] Furthermore, the main shaft pin 8, serving as the rotation fulcrum pin for the locking claw 9, is symmetrically installed through the lower part of the main outer plate 2 of the lock body. During the locking and load-bearing phase, the main shaft pin 8 primarily bears the combined loads of compression and shearing. The locking claw 9 has a symmetrical clamp-shaped lever structure. Under the push and pull of the locking linkage 7, the locking claw 9 rotates and opens around the main shaft pin 8. The inner side of its lower jaw is machined with a bearing surface that matches the locking tongue 10, used for gripping heavy objects. When the electro-permanent magnet assembly 3 demagnetizes, under the action of its own weight, it will forcibly pull open the jaws of the locking claw 9, achieving instantaneous gravity release.

[0037] Furthermore, the bolt 10 is independent of the lock body. The top of the bolt 10 is designed with a mushroom head. During the locking phase, the mushroom head cooperates with the bearing plane of the lock claw 9. During the unlocking and releasing phase, the mushroom head automatically opens the lock claw 9 to achieve gravity unlocking.

[0038] Reference Figure 3 The fixed guide rail 6 is configured with a U-shaped structure, with the protruding part of the U-shaped structure located in the middle of the electro-permanent magnet assembly 3. Multiple countersunk holes are evenly arranged vertically in the middle part of the U-shaped structure, and bolts are inserted into these countersunk holes to connect it to the main outer plate 2 of the lock body. The fixed guide rail 6 mainly serves as a longitudinal guide and does not move relative to other components during the unlocking and subsequent lock tongue 10 reset phases.

[0039] Furthermore, the main outer plate 2 of the lock body is configured as a double-sided clamping plate structure, and each side of the main outer plate 2 of the lock body is provided with a fixed guide rail 6.

[0040] The working principle of the automatic reset gravity release locking mechanism for drop testing described in this application is explained below.

[0041] Reference Figure 7 In the dead-point locking state, the connection point between the locking link 7 and the locking block 4 is lower than the connection point between the locking link 7 and the locking claw 9. That is, there is an angle θ (1-3°) between the locking link 7 and the electro-permanent magnet assembly 3, and the angle is small. This allows the release locking mechanism to ensure a large locking force under a small electromagnetic force, while avoiding the formation of a complete dead-point structure that would prevent smooth unlocking and release. At this time, the locking link 7 can be simplified to a two-force member. The electromagnet selection calculation method is as follows: (1), (2), In the formula, F1 is the weight of the load, L1 and L2 are the lengths of the first and second lever arms, respectively, F2 is the axial force of the locking link 7, F3 is the required electromagnetic force, and θ is the included angle. Calculations show that the electromagnetic force required by the electromagnet is much smaller than the weight of the load, thus enabling reliable locking by overcoming the weight of the push rod 5 with a smaller electromagnetic force.

[0042] In the dead-point locking state, there is no angle between the locking block 4 and the electro-permanent magnet assembly 3. They are horizontal and connected by magnetic force. The purpose of the angle between the locking link 7 and the electro-permanent magnet assembly 3 is to ensure that the electromagnetic force required for locking is much less than the load-bearing weight. This makes the permanent magnet selection lighter, saves space, and enhances reliability.

[0043] Release process: Upon receiving the release signal, the electro-permanent magnet assembly 3 is energized and demagnetized. The energy storage spring 52 exerts a downward force on the locking block 4, causing it to move rapidly downwards. The locking claw 9 opens quickly under the impact of its own weight and rotates around the main shaft pin 8. Driven by the locking linkage 7, the locking block 4 descends continuously along the fixed guide rail 6. At this time, the locking tongue 10 disengages, releasing the load. After falling, the locking release state is as follows: Figure 8 As shown in Figure (b) of the document.

[0044] Automatic Reset Process: After deployment, the latch 10 is located on the bottom lifting frame. At this time, under the action of the hydraulic lifting actuator 0, the release lock begins to descend rapidly. Upon reaching the vicinity of the latch 10, the hydraulic lifting actuator 0 begins to descend slowly. The latch 10 then pushes the locking block 4 upwards via the top rod 5 until the locking claw 9 completely clamps the latch 10. At this point, the electro-permanent magnet assembly 3 is de-energized and magnetized, attracting the locking block 4, thus releasing the lock and achieving the locking state. Figure 8 As shown in Figure (a).

[0045] The automatic reset gravity-release locking mechanism for drop testing provided in this application adopts an near-dead-point locking mechanism, which can provide a locking force far greater than the external load under relatively small electromagnetic force. This ensures the stability and reliability of the locking state of large-tonnage aircraft during drop testing, effectively preventing accidental unlocking due to environmental vibration disturbances and meeting the high safety margin requirements of drop testing. Simultaneously, the electromagnetic triggering method results in a short unlocking response time, achieving millisecond-level release, effectively meeting the technical requirements of synchronous unlocking time and repeated release accuracy in repeated drop testing of the entire aircraft. Furthermore, it features an automatic reset function, autonomously restoring to the initial locked state after each drop test, eliminating the need for manual climbing for secondary locking operations. This significantly improves the efficiency of repeated drop testing of the entire aircraft and effectively reduces the risks of high-altitude operations and manual maintenance costs.

[0046] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. An automatically reset gravity-release locking mechanism for drop tests, characterized in that, The lock body includes a main outer plate (2), a locking claw (9), and a locking tongue (10). It also includes an electro-permanent magnet assembly (3), a locking block (4), a fixed guide rail (6), and a main shaft pin (8) fixed on the main outer plate (2). The top of the main outer plate (2) is connected to the hydraulic lifting actuator (0) via a first connector. The electro-permanent magnet assembly (3) is located on the upper side of the fixed guide rail (6). The locking block (4) is sleeved and fixed on the top rod (5). The side of the locking block (4) facing the main outer plate (2) cooperates with the fixed guide rail (6). The top rod (5) One end of the rod passes through the electro-permanent magnet assembly (3), and the other end of the top rod (5) is provided with a locking tongue (10). The two sides of the locking block (4) are connected to the upper end of the locking claw (9) through the locking link (7). The middle part of the locking claw (9) is fixed to the main outer plate (2) of the lock body through the main shaft pin (8). The lower end of the locking claw (9) clamps the locking tongue (10). In the locking state, the locking block (4) is connected to the electro-permanent magnet assembly (3) under the action of magnetic force. The position of the connection point between the locking link (7) and the locking block (4) is lower than the position of the connection point between the locking link (7) and the locking claw (9).

2. The automatically reset gravity-release locking mechanism for drop testing according to claim 1, characterized in that, The locking block (4) includes a locking block body (41) and a locking block pin (42). The center of the locking block body (41) is provided with a first through hole along the direction of the release locking mechanism. The locking block body (41) is sleeved on the top rod (5) through the first through hole. The side of the locking block body (41) is provided with an opening groove along the direction of the release locking mechanism. The locking block pin (42) passes vertically through the two side walls of the opening groove. One end of the locking link (7) is connected to the locking block pin (42) located in the opening groove. The other end of the locking link (7) is connected to the upper end of the locking claw (9).

3. The automatically reset gravity-release locking mechanism for drop testing according to claim 2, characterized in that, The locking block (4) also includes a bushing (43). The main body (41) of the locking block has a groove on the side facing the main outer plate (2) of the lock body. The groove cooperates with the fixed guide rail (6). The bushing (43) is fixed in the groove. The bushing (43) is used to reduce the wear and vibration of the locking block (4) when it moves vertically along the fixed guide rail (6).

4. The automatically reset gravity-release locking mechanism for drop testing according to claim 1, characterized in that, The push rod (5) includes a main push rod (54) and a thin push rod. The locking block (4) is sleeved on the thin push rod. The thin push rod passes through the top end of the electro-permanent magnet assembly (3) and is provided with a limiting block (51). An energy storage component is sleeved on the thin push rod between the locking block (4) and the electro-permanent magnet assembly (3). The energy storage component is used to quickly release energy when the release command is triggered, drive the main push rod (54) to move downward, and drive the locking link (7) to cross the mechanical dead point, so as to realize rapid unlocking and release.

5. The automatically reset gravity-release locking mechanism for drop testing according to claim 4, characterized in that, The top rod (5) also includes a connecting flange (53), which is fixedly sleeved on the main top rod (54). The bottom of the locking block (4) is fixedly connected to the top rod (5) through the connecting flange (53).

6. The automatically reset gravity-release locking mechanism for drop testing according to claim 4, characterized in that, The energy storage component is set as an energy storage spring (52).

7. The automatically reset gravity-release locking mechanism for drop testing according to claim 1, characterized in that, The locking claw (9) is configured as a symmetrical clamp-shaped lever structure, and the lower jaw of the clamp-shaped lever structure is provided with a bearing plane that matches the locking tongue (10).

8. The automatically reset gravity-release locking mechanism for drop testing according to claim 7, characterized in that, The top of the latch (10) is designed with a mushroom head. During the locking phase, the mushroom head cooperates with the bearing plane of the lock claw (9). During the unlocking and releasing phase, the mushroom head automatically opens the lock claw (9) to achieve gravity unlocking.

9. The automatically reset gravity-release locking mechanism for drop testing according to claim 1, characterized in that, The fixed guide rail (6) is set as a convex shape structure, and the protruding part of the convex shape structure is located in the middle of the electro-permanent magnet assembly (3); multiple countersunk holes are evenly arranged vertically in the middle part of the convex shape structure, and the main outer plate (2) of the lock body is connected by inserting bolts into the countersunk holes.

10. The automatically reset gravity-release locking mechanism for drop testing according to claim 1, characterized in that, The main outer plate (2) of the lock body is set as a double-sided clamping plate structure, and each side of the main outer plate (2) of the lock body is provided with a fixed guide rail (6).

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