Operating mechanism and circuit breaker

Abstract

The present application provides an operating mechanism and a circuit breaker, which belong to the technical field of electrical equipment. The operating mechanism provided by the present application includes: a trigger assembly, a guide shaft, an aircraft lever and a closing half-shaft. The trigger assembly includes a shunt release and a closing / opening release. The guide shaft is located on the same side of the shunt release and the closing / opening release, and the position of the guide shaft is fixed. The aircraft lever is provided with a guide groove, and the aircraft lever is sleeved on the guide shaft through the guide groove. A first drive part is provided on the side of the aircraft lever close to the shunt release. The closing half-shaft is provided on the side of the aircraft lever close to the shunt release. The operating mechanism provided by the present application can disconnect the current of the circuit breaker through the shunt release, and can also disconnect the current of the circuit breaker through the closing / opening release. The closing / opening release can provide a second level of protection for the disconnection of the circuit breaker current, thereby improving the reliability of the circuit breaker and reducing the probability of safety accidents.

Description

Technical Field

[0001] The present application relates to the technical field of electrical equipment, and in particular to an operating mechanism and a circuit breaker. Background Art

[0002] A circuit breaker is a mechanical switch that can connect, carry and disconnect current under normal circuit conditions, and can also connect or disconnect current under specified abnormal circuit conditions.

[0003] In existing technology, automatic opening and closing of circuit breakers typically utilize two trips: a shunt trip for opening and a closing trip for closing, thereby achieving both closing and opening operations. However, in some critical use cases, a shunt trip failure can potentially cause serious safety incidents. Therefore, an operating mechanism and circuit breaker are urgently needed. Summary of the Invention

[0004] The present application provides an operating mechanism and a circuit breaker, which can improve the reliability of the circuit breaker.

[0005] In a first aspect, the present application provides an operating mechanism for use in a circuit breaker, the operating mechanism comprising: a trigger assembly, a guide shaft, an aircraft lever, and a closing half-shaft.

[0006] The trigger assembly includes a shunt release and a closing / opening release. A guide shaft is located on the same side of the shunt release and the closing / opening release, and its position is fixed. A lever is provided with a guide groove, through which the lever is mounted on the guide shaft. The lever can move on the guide shaft in the direction in which the shunt release and the closing / opening release are arranged. A first drive unit is provided on the side of the lever closest to the shunt release. A closing half-shaft is provided on the side of the lever closest to the shunt release.

[0007] The shunt release pushes against the closing half-shaft, causing it to rotate, opening the circuit breaker. Alternatively, when the aircraft lever moves along the arrangement direction until it can mate with the closing half-shaft, the closing / opening release pushes against the first drive unit, causing it to move in the operating direction of the closing / opening release. When the first drive unit moves in the operating direction, it pushes against the closing half-shaft, causing it to rotate, opening the circuit breaker. The operating direction, arrangement direction, and axial direction of the guide shaft are mutually perpendicular.

[0008] Through the above scheme, the present application sets a shunt release and a closing / opening release in the operating mechanism, which can play a dual protection role in disconnecting the circuit breaker current. When the operating mechanism is in a normal state, the shunt release or the closing / opening release can be used to disconnect the current of the circuit breaker. When the shunt release in the operating mechanism fails or is damaged, the closing / opening release can be used to disconnect the current of the circuit breaker. In this way, the reliability of the circuit breaker can be improved and the probability of safety accidents can be reduced.

[0009] A first drive unit is provided on the side of the aircraft lever near the shunt release. When the aircraft lever moves toward the shunt release until it mates with the closing half-shaft, the first drive unit drives the closing half-shaft to rotate, thereby shunting the contact assembly and disconnecting the circuit breaker current. The provision of the first drive unit enables the operating mechanism to disconnect the circuit breaker current using the closing / opening release, increasing the reliability of the operating mechanism and, consequently, the circuit breaker.

[0010] In one possible design, the aircraft lever includes a main body, and the first drive portion is a drive rod extending from the main body toward the closing half-axis. When the aircraft lever moves along the arrangement direction toward the closing half-axis, the first drive portion and the closing half-axis have overlapping projections in the direction of movement.

[0011] With the above solution, the aircraft lever is configured as a combination of a main body and a first drive portion, and the first drive portion is configured as a drive rod. A drive rod extending in the direction of the closing half-axis is provided on the aircraft lever. When the aircraft lever moves, the drive rod drives the drive plate, thereby rotating the closing half-axis. This achieves the purpose of utilizing the closing / opening release to drive the aircraft lever, thereby rotating the closing half-axis to complete the opening operation, thereby improving the reliability of the operating mechanism. By aligning the projections of the first drive portion and the closing half-axis in the direction of operation, the reliability of the aircraft lever is enhanced, reducing the probability of misalignment between the aircraft lever and the closing half-axis, which could result in the circuit breaker failing to disconnect current when the closing / opening release is used, thereby improving the reliability of the circuit breaker.

[0012] In one possible design, the guide groove is a waist-shaped groove, and the dimension of the waist-shaped groove in the direction of movement is larger than the diameter of the guide shaft. The operating mechanism also includes a housing and a first elastic member, wherein a first end of the first elastic member is fixed to the housing, and a second end of the first elastic member is fixed to the aircraft lever.

[0013] With the above solution, the guide groove is set as a waist-shaped groove, so that the aircraft lever can slide along the setting direction of the guide groove during the movement of the aircraft lever. The size of the waist-shaped groove in the action direction is larger than the diameter of the guide shaft, so that when the action end of the closing / opening release pushes against the aircraft lever, the aircraft lever can have a margin of movement, thereby reducing the probability of the aircraft lever being unable to push the closing half-shaft due to interference caused by the guide groove being too small, thereby increasing the reliability of the operating mechanism and thus increasing the reliability of the circuit breaker.

[0014] When the aircraft lever pushes the closing half-shaft to complete the opening operation of the circuit breaker, the aircraft lever stretches the first elastic member in the direction of action, causing the first elastic member to deform. After the circuit breaker completes the opening operation, the first elastic member generates an elastic force when it recovers its deformation. Under the action of the elastic force, the first elastic member drives the aircraft lever to move in a direction opposite to the direction of action, thereby driving the aircraft lever to reset. In this way, the reliability of the aircraft lever can be increased and the probability of the aircraft lever failing to reset after driving the closing half-shaft to rotate is reduced.

[0015] In one possible design, the operating mechanism further includes a closing indicator, which is disposed on one side of the aircraft lever. A shift lever is disposed on the side of the closing indicator facing the aircraft lever. The aircraft lever also includes a first driven portion, which is connected to the side of the main body facing the closing indicator. When the circuit breaker switches from the closed state to the open state, the shift lever shifts the first driven portion, causing the aircraft lever to move to mate with the closing half-axis.

[0016] According to the above solution, a toggle lever is provided on the closing half-shaft, a first driven part is provided on the aircraft lever, the toggle lever is arranged toward the aircraft lever, and the first driven part is arranged toward the closing half-shaft. When the circuit breaker switches from the closed state to the open state, the closing indicator can drive the aircraft lever to a position corresponding to the aircraft lever and the closing half-shaft during the movement. Subsequently, the aircraft lever can be triggered by the closing / opening release, so that the aircraft lever pushes the closing half-shaft to complete the opening of the circuit breaker.

[0017] This arrangement can achieve the effect of reusing the closing indicator, and can reduce the setting of additional driving parts added to drive the aircraft lever, thereby reducing the manufacturing cost of the operating mechanism and thus reducing the use cost of the circuit breaker.

[0018] In a possible design, the first driven part is an arc-shaped plate.

[0019] With this solution, when the detent lever moves the first driven part, the curved surface of the first driven part can better conform to the surface of the detent lever, increasing the contact area between the detent lever and the first driven part, making force transmission between the two parts more reliable. Furthermore, the increased contact area between the detent lever and the first driven part reduces the probability of contact failure between the detent lever and the first driven part due to shaking of the detent lever. The curved surface of the first driven part also reduces the impact force of the detent lever on the first driven part, thereby increasing the service life of the first driven part and the detent lever, thereby increasing the service life of the circuit breaker.

[0020] In one possible design, the operating mechanism also includes a closing release and an energy storage half-shaft. The closing release is located on the side of the closing / opening release away from the shunt release, and the energy storage half-shaft is located on the side of the aircraft lever closer to the closing release. A second drive unit is provided on the side of the aircraft lever closer to the closing release. When the aircraft lever moves along the arrangement direction until it can engage the energy storage half-shaft, the closing release or the closing / opening release pushes against the second drive unit, causing it to move in the direction of operation. As the second drive unit moves in the direction of operation, it pushes against the energy storage half-shaft, causing it to rotate, closing the circuit breaker.

[0021] Through the above-mentioned solution, the operating mechanism of the present application is also provided with a closing release and an energy storage half-shaft. When the aircraft lever moves to a position where it can cooperate with the energy storage half-shaft, the closing release can drive the aircraft lever to move, and the second drive portion provided on the aircraft lever can be used to push the energy storage half-shaft to rotate, thereby closing the circuit breaker. This arrangement can provide dual protection for the closing of the circuit breaker through the closing release and the closing / opening release. When the operating mechanism is in a normal state, the closing release or the closing / opening release is used to close the circuit breaker. When the closing release fails or is damaged, the closing / opening release is used to close the circuit breaker. This increases the reliability of the circuit breaker and reduces the probability of production accidents caused by the circuit breaker's inability to close.

[0022] In one possible design, the operating mechanism further includes an energy storage indicator disposed on one side of the aircraft lever. The aircraft lever also includes a second driven portion connected to the side of the main body facing the energy storage indicator. When the circuit breaker switches from the closed state to the open state, the energy storage indicator drives the second driven portion, causing the aircraft lever to move to mate with the energy storage half-shaft.

[0023] Through the above solution, during the energy storage process of the circuit breaker, the energy storage indicator moves toward the indicator window inside the circuit breaker casing. At the same time, the energy storage indicator drives the aircraft lever to move along the arrangement direction of the closing release, the closing / opening release, and the shunt release until the aircraft lever can cooperate with the energy storage half-shaft. Subsequently, the aircraft lever can be triggered by the closing release or the closing / opening release, so that the aircraft lever pushes the energy storage half-shaft to complete the opening of the circuit breaker.

[0024] This arrangement can achieve the effect of reusing the energy storage indicator, reduce the number of additional driving parts added to drive the aircraft lever, reduce the manufacturing cost of the operating mechanism, and thus reduce the use cost of the circuit breaker.

[0025] In one possible design, the operating mechanism further includes a housing and a second elastic member, wherein a first end of the second elastic member is fixed to the housing, a second end of the second elastic member is fixed to the aircraft lever, and the second spring is used to drive the aircraft lever to move toward the energy storage half-axis.

[0026] Through the above scheme, the second elastic member is stretched by utilizing the movement of the aircraft lever toward the closing half-axis. During this process, the second elastic member is deformed. When the aircraft lever needs to move toward the energy storage half-axis, the elastic force generated when the second elastic member recovers its deformation can pull the aircraft lever toward the energy storage half-axis. In this way, the aircraft lever can be assisted in its movement toward the energy storage half-axis.

[0027] In one possible design, a drive plate is provided on the closing half-shaft, and a boss is provided on the energy storage half-shaft. When the aircraft lever pushes against the closing half-shaft, the first drive unit contacts the drive plate. When the aircraft lever pushes against the energy storage half-shaft, the second drive unit contacts the boss.

[0028] Through the above solution, a drive plate is provided on the closing half-shaft, so that the aircraft lever can better drive the closing half-shaft to rotate, and a boss is provided on the energy storage half-shaft, so that the aircraft lever can better drive the energy storage half-shaft to rotate. This arrangement improves the reliability of the operating mechanism, thereby improving the reliability of the circuit breaker.

[0029] In a second aspect, the present application provides a circuit breaker, comprising the operating mechanism mentioned in the first aspect.

[0030] Through the above scheme, the operating mechanism provided by the present application can disconnect the current of the circuit breaker through the shunt release, and the operating mechanism provided by the present application can also disconnect the current of the circuit breaker through the closing / opening release. In this way, on the basis of ensuring that the circuit breaker can normally connect or disconnect the current, the closing / opening release can also provide a second level of protection for the disconnection of the circuit breaker current. When the shunt release of the circuit breaker is damaged or fails, the closing / opening release can be used to disconnect the current of the circuit breaker, thereby improving the reliability of the circuit breaker and reducing the probability of safety accidents.

[0031] The beneficial effects of the circuit breaker provided in the second aspect can be referred to the beneficial effects brought about by the first aspect and the various possible implementation methods of the first aspect, and will not be repeated here. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 This is a schematic diagram of the overall structure of the operating mechanism provided in an embodiment of the present application.

[0033] Figure 2 A schematic diagram of a portion of the structure of the operating mechanism provided in an embodiment of the present application.

[0034] Figure 3 for Figure 2 Magnified view of section A.

[0035] Figure 4 A schematic structural diagram of an aircraft lever provided in an embodiment of the present application at one viewing angle.

[0036] Figure 5 A schematic diagram of a portion of the structure of the operating mechanism of the circuit breaker provided in an embodiment of the present application when in the disconnected state.

[0037] Figure 6 A schematic diagram of the internal structure of the operating mechanism provided in an embodiment of the present application.

[0038] Figure 7 A schematic structural diagram of the aircraft lever provided in an embodiment of the present application from another perspective.

[0039] Figure 8 A schematic diagram of a portion of the structure of the operating mechanism of the circuit breaker provided in an embodiment of the present application when the circuit breaker is in a closed state.

[0040] Description of reference numerals:

[0041] 100. Operating mechanism;

[0042] 200, trigger assembly; 210, shunt release; 220, closing / opening release; 230, closing release;

[0043] 300, guide shaft;

[0044] 400, aircraft lever; 410, guide groove; 420, first driving portion; 430, main body; 440, first driven portion; 450, second driving portion;

[0045] 500, closing half shaft; 510, driving plate;

[0046] 600, housing; 610, first elastic member; 620, second elastic member;

[0047] 700, closing indicator; 710, shift lever;

[0048] 800, energy storage half shaft; 810, boss;

[0049] 900. Energy storage indicator. DETAILED DESCRIPTION

[0050] To make the purpose, technical solutions, and advantages of the embodiments of this application more clear, the technical solutions in the embodiments of this application will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of this application. Obviously, the described embodiments are part of the embodiments of this application, not all of the embodiments. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of this application.

[0051] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by those skilled in the art to which this application belongs; the terms used in the specification of the application herein are only for the purpose of describing specific embodiments and are not intended to limit this application.

[0052] The terms "comprises", "comprising" and "having" and any variations thereof in the specification, claims and drawings of this application are intended to cover but not exclude other contents. The word "a" or "an" does not exclude the presence of a plurality.

[0053] References to "embodiments" herein mean that a particular feature, structure, or characteristic described in connection with the embodiments may be included in at least one embodiment of the present application. The appearance of the phrase "embodiment" in various places in the specification does not necessarily refer to the same embodiment, nor does it necessarily refer to independent or alternative embodiments that are mutually exclusive of other embodiments. It is understood, both explicitly and implicitly, by those skilled in the art that the embodiments described herein may be combined with other embodiments.

[0054] The term "and / or" in this document simply describes a relationship between related objects, indicating that three possible relationships exist. For example, "A and / or B" can mean: A exists alone, A and B exist simultaneously, or B exists alone. Additionally, the character " / " in this document generally indicates that the related objects are in an "or" relationship.

[0055] The directional words appearing in the following description are all directions shown in the drawings, and do not limit the specific structure of the static contact of a circuit breaker and the circuit breaker of the present application. For example, in the description of the present application, the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate directions or positional relationships based on the directions or positional relationships shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as limiting the present application.

[0056] In addition, the terms "first", "second", etc. in the description and claims of this application or the above-mentioned drawings are used to distinguish different objects, rather than to describe a specific order, and may explicitly or implicitly include one or more such features.

[0057] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "install", "connect" and "connect" should be understood in a broad sense. For example, the "connection" or "connection" of a mechanical structure may refer to a physical connection. For example, the physical connection may be a fixed connection, such as a fixed connection through a fixing part, such as a fixed connection through a screw, bolt or other fixing part; the physical connection may also be a detachable connection, such as a mutual snap-on or snap-fit ​​connection; the physical connection may also be an integral connection, for example, a connection formed by welding, bonding or integral molding. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0058] In order to enable those skilled in the art to better understand the solution of the present application, the technical solution in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings.

[0059] Figure 1 This is a schematic diagram of the overall structure of the operating mechanism provided in the embodiment of the present application. Figure 1 As shown, the present application provides a circuit breaker, which includes an operating mechanism.

[0060] A circuit breaker is a mechanical switch that can connect, carry, and disconnect current under normal circuit conditions, as well as under specified abnormal circuit conditions. A circuit breaker includes a housing and a contact assembly. The housing generally includes a base and a cover. The cover, when closed onto the base, forms an installation space within which the contact assembly and operating mechanism 100 are located.

[0061] Operating mechanism 100 includes a shunt release 210 and a closing / opening release 220. Shunt release 210 triggers a mechanism within the circuit breaker, causing the contact assembly to shunt, thereby disconnecting the circuit breaker current. Closing / opening release 220 triggers a mechanism within the circuit breaker, causing the contact assembly to close or shunt, thereby connecting or disconnecting the circuit breaker current.

[0062] To sum up, the operating mechanism 100 provided in the present application can not only disconnect the current of the circuit breaker through the shunt release 210, but also connect or disconnect the current of the circuit breaker through the closing / opening release 220. In this way, on the basis of ensuring that the circuit breaker can normally connect or disconnect the current, the closing / opening release 220 can also provide a second level of protection for the disconnection of the circuit breaker current. When the shunt release 210 of the circuit breaker is damaged or fails, the closing / opening release 220 can be used to disconnect the current of the circuit breaker, thereby improving the reliability of the circuit breaker and reducing the probability of safety accidents.

[0063] The operating mechanism 100 mentioned in the embodiment of the present application will be clearly and completely described below with reference to the accompanying drawings.

[0064] Figure 2 A schematic diagram of a portion of the structure of the operating mechanism provided in an embodiment of the present application. Figure 3 for Figure 2 Magnified view of section A.

[0065] like Figure 2 as well as Figure 3 As shown, the present application provides an operating mechanism 100 for use in a circuit breaker. The operating mechanism 100 includes a trigger assembly 200 , a guide shaft 300 , an aircraft lever 400 , and a closing half-shaft 500 .

[0066] The trigger assembly 200 includes a shunt release 210 and a closing / opening release 220. A guide shaft 300 is located on the same side of the shunt release 210 and the closing / opening release 220, and the position of the guide shaft 300 is fixed. A lever 400 is provided with a guide slot 410, through which the lever 400 is mounted and mounted on the guide shaft 300. The lever 400 is movable on the guide shaft 300 in the direction of alignment of the shunt release 210 and the closing / opening release 220. A first drive unit 420 is provided on the side of the lever 400 near the shunt release 210. A closing half-shaft 500 is provided on the side of the lever 400 near the shunt release 210.

[0067] The shunt release 210 pushes against the closing half-shaft 500, causing it to rotate, opening the circuit breaker. Alternatively, when the aircraft lever 400 moves along the arrangement direction until it can mate with the closing half-shaft 500, the closing / opening release 220 pushes against the first drive unit 420, causing it to move along the operating direction of the closing / opening release 220. As the first drive unit 420 moves along the operating direction, it pushes against the closing half-shaft 500, causing it to rotate, opening the circuit breaker. The operating direction, arrangement direction, and axial direction of the guide shaft 300 are perpendicular to each other.

[0068] Trigger assembly 200 is used to trigger the internal mechanism of the circuit breaker, closing or opening the contact assembly to connect or disconnect the circuit breaker current. Trigger assembly 200 includes a shunt release 210 and a closing / opening release 220. Both shunt release 210 and closing / opening release 220 are equipped with an actuating terminal, which is used to trigger the internal mechanism of the circuit breaker.

[0069] The operating mechanism 100 includes a housing 600 . The housing 600 may be a U-shaped structure formed by sequentially connecting a first side panel, a second side panel, and a third side panel, wherein the first side panel is arranged in parallel with the third side panel.

[0070] The guide shaft 300 can be a columnar structure, one end of the guide shaft 300 is fixed on the first side plate, and the guide shaft 300 is arranged on the side close to the action end of the shunt release 210 and the closing / opening release 220, and the extension direction of the guide shaft 300 is perpendicular to the arrangement direction of the shunt release 210 and the closing / opening release 220.

[0071] The guide groove 410 can be a through groove provided on the aircraft lever 400 along the axis of the guide shaft 300. The guide groove 410 can be integrally formed with the aircraft lever 400, or the guide groove 410 can be provided on the aircraft lever 400 after the aircraft lever 400 is formed by grooving or engraving. The first drive unit 420 can be a drive structure provided on the aircraft lever 400, and the first drive unit 420 can move along with the aircraft lever 400.

[0072] The closing half shaft 500 is used to control the contact assembly of the circuit breaker to open. The closing half shaft 500 can be a columnar structure, and the closing half shaft 500 is rotatably connected to the first side plate and the third side plate respectively.

[0073] There are two methods for breaking the current of the circuit breaker in this application.

[0074] The first method uses the shunt release 210. For example, when the aircraft lever 400 moves to the open position, the actuating end of the shunt release 210 pushes against the closing half-shaft 500, causing the closing half-shaft 500 to rotate and drive the contact assembly to open, thereby opening the circuit breaker and disconnecting the current.

[0075] The second method uses the closing / opening release 220. Because the closing / opening release 220 is located on the side of the shunt release 210 away from the closing half-shaft, the aircraft lever 400 is required to assist in the opening operation using the closing / opening release 220. When the aircraft lever 400 moves toward the side of the shunt release 210 until it mates with the closing half-shaft 500, the first drive unit 420 aligns with the position of the closing half-shaft 500. At this point, the actuating end of the closing / opening release 220 pushes against the first drive unit 420, driving the first drive unit 420 to move in the actuating direction of the closing / opening release 220. This causes the first drive unit 420 to push against the closing half-shaft 500 to rotate, opening the circuit breaker and interrupting the current.

[0076] In summary, the present application sets a shunt release 210 and a closing / opening release 220 in the operating mechanism 100, which can play a dual protection role in the disconnection of the circuit breaker current. When the operating mechanism 100 is in a normal state, the shunt release 210 or the closing / opening release 220 can be used to disconnect the current of the circuit breaker. When the shunt release 210 in the operating mechanism 100 fails or is damaged, the closing / opening release 220 can be used to disconnect the current of the circuit breaker. In this way, the reliability of the circuit breaker can be improved and the probability of safety accidents can be reduced.

[0077] A first drive unit 420 is provided on the side of the aircraft lever 400 near the shunt release 210. When the aircraft lever 400 moves toward the shunt release 210 and engages with the closing half-shaft 500, the first drive unit 420 drives the closing half-shaft 500 to rotate, thereby shunting the contact assembly and disconnecting the circuit breaker current. The provision of the first drive unit 420 enables the operating mechanism 100 to disconnect the circuit breaker current using the closing / opening release 220, thereby increasing the reliability of the operating mechanism 100 and, consequently, the reliability of the circuit breaker.

[0078] The structure of the aircraft lever 400 will be described below with reference to the accompanying drawings.

[0079] Figure 4 A schematic structural diagram of an aircraft lever provided in an embodiment of the present application at one viewing angle. Figure 5 This is a partial structural diagram of the operating mechanism of the circuit breaker provided in the embodiment of the present application in the disconnected state. Figure 4 as well as Figure 5As shown, the aircraft lever 400 includes a main body 430, and a first drive portion 420 is a drive rod extending from the main body 430 toward the closing half-shaft 500. After the aircraft lever 400 moves along the arrangement direction toward the closing half-shaft 500, the first drive portion 420 and the closing half-shaft 500 have overlapping projections in the direction of movement.

[0080] The main body 430 may be plate-shaped, and the first driving portion 420 may be a driving rod disposed on the main body 430 toward the closing half-axis 500. The driving rod may be integrally formed with the main body 430, or the driving rod may be formed separately from the main body 430 and then assembled.

[0081] A driving plate 510 is provided on the closing half-shaft 500 . The driving plate 510 may be a plate-shaped structure provided on the closing half-shaft 500 toward the aircraft lever 400 .

[0082] When the first driving part 420 and the driving part have overlapping projections in the direction of movement, the aircraft lever 400 moves toward the side of the shunt release 210 to cooperate with the closing half-shaft 500. In this way, when the closing and opening release 220 triggers the aircraft lever 400, the first driving part 420 can drive the closing half-shaft 500 to rotate.

[0083] Through the above-mentioned arrangement, the aircraft lever 400 is arranged in the form of a combination of the main body 430 and the first drive part 420, and the first drive part 420 is arranged in the form of a drive rod. A drive rod extending toward the closing half-shaft 500 is provided on the aircraft lever 400. When the aircraft lever 400 moves, the drive rod can be used to drive the drive plate 510 and drive the closing half-shaft 500 to rotate, thereby achieving the purpose of using the closing / opening release 220 to drive the aircraft lever 400 and thereby drive the closing half-shaft 500 to rotate to complete the opening action, thereby improving the reliability of the operating mechanism.

[0084] By making the first drive part 420 and the closing half-shaft 500 have overlapping projections in the direction of movement, the reliability of the aircraft lever 400 can be increased, and the probability of the problem of being unable to disconnect the current of the circuit breaker when using the closing / opening release 220 due to misalignment between the aircraft lever 400 and the closing half-shaft 500 is reduced, thereby increasing the reliability of the circuit breaker.

[0085] In order to ensure that the aircraft lever 400 can effectively trigger the closing half-shaft 500, the present application improves the guide groove 410. The structure of the guide groove 410 will be described in detail below with reference to the accompanying drawings.

[0086] like Figure 2 、 Figure 4 as well as Figure 5As shown, the guide groove 410 is a waist-shaped groove, and the dimension of the waist-shaped groove in the direction of movement is larger than the diameter of the guide shaft 300. The operating mechanism 100 also includes a housing 600 and a first elastic member 610. The first end of the first elastic member 610 is fixed to the housing 600, and the second end of the first elastic member 610 is fixed to the aircraft lever 400.

[0087] The guide groove 410 can be a waist-shaped groove and can be arranged along the alignment direction of the shunt release 210 and the closing / opening release 220. This allows the lever 400 to move along the guide groove 410 along the guide shaft 300 in the alignment direction of the shunt release 210 and the closing / opening release 220. For example, when the circuit breaker is closed, the lever 400 moves to abut one end of the waist-shaped groove, and when the circuit breaker is open, the lever 400 moves to abut the other end of the waist-shaped groove. The ends of the guide groove 410 can be arc-shaped grooves to better align the ends of the guide groove 410 with the guide shaft 300. Furthermore, the arc-shaped grooves can reduce the impact force exerted by the lever 400 on the guide groove 410, thereby increasing the lifespan of the lever 400 and the guide groove 410.

[0088] The size of the waist groove in the direction of movement is larger than the diameter of the guide shaft 300. Figure 4 as well as Figure 7 As shown, the width of one end of the waist-shaped groove close to the first driving portion 420 is greater than the width of the other end of the waist-shaped groove.

[0089] The first elastic member 610 can be a spring or elastic cord. The operating mechanism 100 also includes a first fixed shaft. The first fixed shaft and the guide shaft 300 are disposed on the same side plate and are positioned between the closing half-shaft 500 and the guide shaft 300. The first end of the first elastic member 610 is fixedly connected to the first fixed shaft.

[0090] Through the above configuration, the guide groove 410 is configured as a waist-shaped groove, allowing the lever 400 to slide along the direction in which the guide groove 410 is provided during its movement. The waist-shaped groove, in the direction of movement, is larger than the diameter of the guide shaft 300, allowing the lever 400 to move with sufficient margin when the actuating end of the closing / opening release 220 pushes against the lever 400. This reduces the likelihood of interference with the lever 400 due to an undersized guide groove 410, resulting in the lever 400 being unable to push against the closing half-shaft 500. This improves the reliability of the operating mechanism 100, and thus the circuit breaker.

[0091] When the aircraft lever 400 pushes the closing half-shaft 500 to complete the opening operation of the circuit breaker, the aircraft lever 400 stretches the first elastic member 610 in the direction of action, causing the first elastic member 610 to deform. After the circuit breaker completes the opening operation, the first elastic member 610 generates an elastic force when it recovers its deformation. Under the action of the elastic force, the first elastic member 610 drives the aircraft lever 400 to move in a direction opposite to the direction of action, thereby driving the aircraft lever 400 to reset. In this way, the reliability of the aircraft lever 400 can be increased, and the probability of the aircraft lever 400 failing to reset after driving the closing half-shaft 500 to rotate is reduced.

[0092] Figure 6 A schematic diagram of the internal structure of the operating mechanism provided in an embodiment of the present application. Figure 7 This is a schematic diagram of the structure of the aircraft lever provided in the embodiment of the present application from another perspective. Figure 1 、 Figure 6 as well as Figure 7 As shown, the operating mechanism 100 mentioned in this application also includes a closing indicator 700, which is disposed on one side of the aircraft lever 400. A shift lever 710 is disposed on the side of the closing indicator 700 facing the aircraft lever 400. The aircraft lever 400 also has a first driven portion 440, which is connected to the side of the main body 430 facing the closing indicator 700. When the circuit breaker switches from the closed state to the open state, the shift lever 710 shifts the first driven portion 440, causing the aircraft lever 400 to move to mate with the closing half-shaft 500.

[0093] An indicator window is provided on the housing of the circuit breaker. When the circuit breaker is in the closed state, the closing indicator 700 is exposed from the window. When the circuit breaker is in the open state, the closing indicator 700 is hidden in the housing of the circuit breaker.

[0094] The closing indicator 700 is located opposite to the aircraft lever 400 , and the shifting rod 710 may be a rod-shaped structure disposed so that the closing indicator 700 faces the aircraft lever 400 .

[0095] The first driven portion 440 can be a plate-shaped structure that extends from the aircraft lever 400 toward the closing indicator 700. When the circuit breaker switches from the closed state to the open state, the closing indicator 700 moves within the housing until the indicator window no longer displays the closing indicator 700. During this process, the lever 710 moves the first driven portion 440, causing the aircraft lever 400 to stop moving after the projections of the first driving portion 420 and the closing half-axis 500 overlap in the direction of movement.

[0096] The first driven portion 440 may be a curved plate. This arrangement allows the curved surface of the first driven portion 440 to better mate with the surface of the lever 710 when the lever 710 moves the first driven portion 440, increasing the contact area between the lever 710 and the first driven portion 440 and ensuring more reliable force transmission between the lever 710 and the first driven portion 440. Furthermore, the increased contact area between the lever 710 and the first driven portion 440 reduces the probability of contact failure between the lever 710 and the first driven portion 440 due to shaking of the lever 710. The curved surface of the first driven portion 440 also reduces the impact force of the lever 710 on the first driven portion 440, thereby increasing the service life of the first driven portion 440 and the lever 710, and thereby increasing the service life of the circuit breaker.

[0097] To sum up, a toggle lever 710 is provided on the closing half-shaft 500, and a first driven part 440 is provided on the aircraft lever 400. The toggle lever 710 is provided toward the aircraft lever 400, and the first driven part 440 is provided toward the closing half-shaft 500. In the process of switching the circuit breaker from the closed state to the open state, the closing indicator 700 can drive the aircraft lever 400 to move to the position corresponding to the aircraft lever 400 and the closing half-shaft 500 during the movement. Subsequently, the aircraft lever 400 can be triggered by the closing / opening release 220, so that the aircraft lever 400 pushes the closing half-shaft 500 to complete the opening of the circuit breaker.

[0098] This arrangement allows the closing indicator 700 to be reused, and can reduce the number of additional driving components added to drive the aircraft lever 400, thereby reducing the manufacturing cost of the operating mechanism 100 and thus reducing the use cost of the circuit breaker.

[0099] In addition to closing the circuit breaker by the closing / opening release 220, the circuit breaker of the present application can also be closed by setting a closing release. For example, Figure 8 This is a partial structural diagram of the operating mechanism of the circuit breaker in the closed state provided in the embodiment of the present application. Figure 6 as well as Figure 8 As shown, the operating mechanism 100 further includes a closing release 230 and an energy storage half-shaft 800 . The closing release 230 is located on the side of the closing / opening release 220 away from the shunt release, and the energy storage half-shaft 800 is located on the side of the aircraft lever 400 close to the closing release 230 .

[0100] A second drive unit 450 is provided on the side of the aircraft lever 400 near the closing release 230. When the aircraft lever 400 moves along the arrangement direction until it can engage with the energy storage half-shaft 800, the closing release 230 or the closing / opening release 220 pushes against the second drive unit 450, causing it to move in the operating direction. As the second drive unit 450 moves in the operating direction, it pushes against the energy storage half-shaft 800, causing it to rotate, closing the circuit breaker.

[0101] The closing release 230, the closing / opening release 220, and the shunt release 210 are sequentially arranged on the second side plate. The energy storage half shaft 800 is arranged on the side of the aircraft lever 400 close to the closing release 230. In other words, the position of the closing release 230 corresponds to the position of the energy storage half shaft 800.

[0102] The aircraft lever 400 is positioned between the energy storage axle 800 and the closing axle 500. The second drive unit 450 can be a drive structure located on the side of the aircraft lever 400 near the energy storage axle 800. A boss 810 is provided on the energy storage axle 800. The boss 810 can be integrally formed with the axle 800, or it can be separately formed and then assembled. The second drive unit 450 pushes against the boss 810, causing the axle 800 to rotate.

[0103] There are two methods for closing the circuit breaker mentioned in this application. The two methods are described below.

[0104] The first method is that when the aircraft lever 400 moves along the arrangement direction of the closing release 230, the closing / opening release 220 and the shunt release 210 until it can cooperate with the energy storage half-shaft 800, at this time, the second driving part 450 provided on the aircraft lever 400 coincides with the projection part of the closing half-shaft 500 in the movement direction. At this time, the action end of the closing / opening release 220 pushes the aircraft lever 400, and the second driving part 450 of the aircraft lever 400 pushes the energy storage half-shaft 800, causing the energy storage half-shaft 800 to rotate, thereby closing the circuit breaker.

[0105] The second method is that when the aircraft lever 400 moves along the arrangement direction of the closing release 230, the closing / opening release 220 and the shunt release 210 until it can cooperate with the energy storage half-shaft 800, at this time, the second driving part 450 provided on the aircraft lever 400 coincides with the projection part of the closing half-shaft 500 in the movement direction. At this time, the action end of the closing release 230 pushes the aircraft lever 400, and the second driving part 450 of the aircraft lever 400 pushes the energy storage half-shaft 800, causing the energy storage half-shaft 800 to rotate, thereby closing the circuit breaker.

[0106] In summary, the operating mechanism 100 of the present application is further provided with a closing release 230 and an energy storage half-shaft 800. When the aircraft lever 400 moves to a position where it can engage with the energy storage half-shaft 800, the closing release 230 can drive the aircraft lever 400 to move, and the second drive portion 450 provided on the aircraft lever 400 pushes the energy storage half-shaft 800 to rotate, thereby closing the circuit breaker. This arrangement provides dual protection for the closing of the circuit breaker through the closing release 230 and the closing / opening release 220. When the operating mechanism 100 is in a normal state, the closing release 230 or the closing / opening release 220 is used to close the circuit breaker. When the closing release 230 fails or is damaged, the closing / opening release 220 is used to close the circuit breaker. This increases the reliability of the circuit breaker and reduces the probability of production accidents caused by the circuit breaker's inability to close.

[0107] like Figure 1 as well as Figure 6 As shown, the operating mechanism 100 further includes an energy storage indicator 900, which is disposed on one side of the aircraft lever 400. The aircraft lever 400 also includes a second driven portion connected to the side of the body 430 facing the energy storage indicator 900. When the circuit breaker switches from the closed state to the open state, the energy storage indicator 900 drives the second driven portion, causing the aircraft lever 400 to move to mate with the energy storage half-shaft 800.

[0108] The energy storage indicator 900 is disposed on the same side as the aircraft lever 400. The energy storage indicator 900 can move toward the indicator window inside the circuit breaker housing during the energy storage process until the circuit breaker energy storage is completed, at which time the energy storage indicator 900 is exposed from the indicator window.

[0109] The second driven portion may be a protrusion structure provided on the aircraft lever 400 toward the energy storage indicator 900 , or the second driven portion may be a groove structure provided on the aircraft lever 400 .

[0110] To sum up, during the energy storage process of the circuit breaker, the energy storage indicator 900 moves toward the indicator window inside the circuit breaker housing. At the same time, the energy storage indicator 900 drives the aircraft lever 400 to move along the arrangement direction of the closing release 230, the closing / opening release 220, and the shunt release 210 until the aircraft lever 400 can cooperate with the energy storage half-shaft 800. Subsequently, the aircraft lever 400 can be triggered by the closing release 230 or the closing / opening release 220, so that the aircraft lever 400 pushes the energy storage half-shaft 800 to complete the opening of the circuit breaker.

[0111] This arrangement allows the energy storage indicator 900 to be reused, and can reduce the number of additional driving components added to drive the aircraft lever 400, thereby reducing the manufacturing cost of the operating mechanism 100 and thus reducing the use cost of the circuit breaker.

[0112] like Figure 2 as well as Figure 3 As shown, the operating mechanism 100 further includes a second elastic member 620. The first end of the second elastic member 620 is fixed to the housing 600, and the second end of the second elastic member 620 is fixed to the aircraft lever 400. The second spring is used to drive the aircraft lever 400 to move toward the energy storage half shaft 800.

[0113] The operating mechanism 100 also has a second fixed shaft, which is mounted on the first side panel and on the same side as the guide shaft 300. The second fixed shaft is positioned near the energy storage half-shaft 800. A second elastic member 620 can be a spring or elastic cord. One end of the second elastic member 620 is fixedly connected to the second fixed shaft, and the other end is fixedly connected to the aircraft lever 400.

[0114] When the aircraft lever 400 moves toward the closing half-shaft 500, the second elastic member 620 is gradually stretched. When the aircraft lever 400 moves toward the energy storage half-shaft 800, the second elastic member 620 recovers its deformation. During the process of the second elastic member 620 recovering its deformation, the elastic force generated by the second elastic member 620 pulls the aircraft lever 400 toward the energy storage half-shaft 800.

[0115] Through the above-mentioned arrangement, the second elastic member 620 is stretched by utilizing the movement of the aircraft lever 400 toward the closing half-shaft 500. During this process, the second elastic member 620 is deformed. When the aircraft lever 400 needs to move toward the energy storage half-shaft 800, the elastic force generated when the second elastic member 620 recovers its deformation can pull the aircraft lever 400 toward the energy storage half-shaft 800. In this way, the aircraft lever 400 can be assisted in its movement toward the energy storage half-shaft 800.

Claims

1. An operating mechanism, applied to a circuit breaker, characterized in that: The operating mechanism includes: Trigger components, including shunt release and closing / opening release; A guide shaft is located on the same side of the shunt release and the closing / opening release, and the position of the guide shaft is fixed; An aircraft lever is provided with a guide groove, the aircraft lever is sleeved on the guide shaft through the guide groove, and the aircraft lever is capable of moving on the guide shaft along the arrangement direction of the shunt release and the closing / opening release; a first driving portion is provided on a side of the aircraft lever close to the shunt release; a closing half-shaft, provided on a side of the aircraft lever close to the shunt release; The shunt release pushes the closing half-shaft and drives the closing half-shaft to rotate, so as to open the circuit breaker; Alternatively, when the aircraft lever moves along the arrangement direction until the aircraft lever is able to cooperate with the closing half-shaft, the closing / opening release pushes the first driving part and causes the first driving part to move along the action direction of the closing / opening release; when the first driving part moves along the action direction, it pushes the closing half-shaft and drives the closing half-shaft to rotate, thereby opening the circuit breaker; The movement direction, the arrangement direction, and the axial direction of the guide shaft are perpendicular to each other.

2. The operating mechanism according to claim 1, characterized in that: The aircraft lever comprises a main body, and the first driving portion is a driving rod extending from the main body toward one side of the closing half-axis; After the aircraft lever moves toward the closing half-axis along the arrangement direction, the first driving portion and the closing half-axis have overlapping projections in the movement direction.

3. The operating mechanism according to claim 1, characterized in that: The guide groove is a waist-shaped groove, and the size of the waist-shaped groove in the movement direction is larger than the diameter of the guide shaft; The operating mechanism further includes a housing and a first elastic member, wherein a first end of the first elastic member is fixed to the housing, and a second end of the first elastic member is fixed to the aircraft lever.

4. The operating mechanism according to claim 2, characterized in that: The operating mechanism further includes a closing indicator, which is arranged on one side of the aircraft lever, and a shifting rod is arranged on the side of the closing indicator facing the aircraft lever; The aircraft lever is further provided with a first driven portion, which is connected to a side of the main body facing the closing indicator; When the circuit breaker is switched from a closed state to an open state, the switching rod switches the first driven part, so that the aircraft lever moves to cooperate with the closing half-shaft.

5. The operating mechanism according to claim 4, characterized in that: The first driven part is an arc-shaped plate.

6. The operating mechanism according to claim 2, characterized in that: The operating mechanism further includes a closing release and an energy storage half-shaft, wherein the closing release is located on a side of the closing / opening release away from the shunt release, and the energy storage half-shaft is located on a side of the aircraft lever close to the closing release; A second driving portion is provided on a side of the aircraft lever close to the closing release; When the aircraft lever moves along the arrangement direction until it can cooperate with the energy storage half-shaft, the closing release or the opening / closing release pushes the second driving part and causes the second driving part to move along the action direction; when the second driving part moves along the action direction, it pushes the energy storage half-shaft and drives the energy storage half-shaft to rotate, so that the circuit breaker is closed.

7. The operating mechanism according to claim 6, characterized in that: The operating mechanism further includes an energy storage indicator, which is arranged on one side of the aircraft lever; The aircraft lever further includes a second driven portion connected to a side of the main body facing the energy storage indicator; When the circuit breaker is switched from a closed state to an open state, the energy storage indicator drives the second driven part to move the aircraft lever to cooperate with the energy storage half-shaft.

8. The operating mechanism according to claim 6 or 7, characterized in that: The operating mechanism further includes a housing and a second elastic member; The first end of the second elastic member is fixed to the housing, and the second end of the second elastic member is fixed to the aircraft lever. The second elastic member is used to drive the aircraft lever to move toward the direction close to the energy storage half-axis.

9. The operating mechanism according to claim 6, characterized in that: A driving plate is provided on the closing half-shaft, and a boss is provided on the energy storage half-shaft; When the aircraft lever pushes the closing half-shaft, the first driving part contacts the driving plate; When the aircraft lever pushes the energy storage half shaft, the second driving part contacts the boss.

10. A circuit breaker, characterized in that: The invention comprises an operating mechanism according to any one of claims 1 to 9.

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