Locking structure and horizontal stabilizer trim actuator

Abstract

The embodiment of the invention discloses a locking structure and a horizontal stabilizer trim actuator, the locking structure is applied to the horizontal stabilizer trim actuator, and the horizontal stabilizer trim actuator comprises a hollow rolling screw rod. The locking structure comprises a locking rod and a connector. The locking rod is provided with a first rod and a second rod which are connected, the first rod is used for being arranged in the rolling lead screw in a penetrating mode and fixedly connected with the rolling lead screw, and the second rod is used for penetrating out of the rolling lead screw. The connector comprises a limiting shell, and the limiting shell is arranged on the second rod in a sleeving mode and connected with the second rod in a sliding mode. A plurality of limiting groove sets are formed in the second rod at intervals in the axial direction of the locking rod, safety positions are formed in the intervals between the adjacent limiting groove sets, limiting notches are formed in the peripheral wall of the limiting shell, limiting blocks are arranged in the limiting notches, and when the second rod rotates, the projection of the limiting blocks on the second rod is overlapped with the safety positions. When the second rod slides in the axial direction of the locking rod, the limiting block is embedded in the limiting groove set.

Description

Technical Field

[0001] The present invention relates to the technical field of electromechanical actuators, and in particular to a locking structure and a horizontal stabilizer trim actuator. Background Art

[0002] The horizontal stabilizer is a pair of horizontally placed wing surfaces, usually located below or on both sides of the vertical tail. It is part of the tail of the aircraft and is used to provide stability and maneuverability in the pitch direction. The horizontal stabilizer trim actuator (HSTA) is an electromechanical device used to adjust the angle of the horizontal stabilizer of the aircraft. Its main function is to optimize the balance and stability of the aircraft under different flight conditions by changing the inclination angle of the horizontal stabilizer (called the trim angle).

[0003] The current horizontal stabilizer trim actuator (HSTA) generally transmits the load to the fuselage structure and wing surface respectively via universal joints and ball screws. If these structures (universal joints or ball screws) fail, the horizontal stabilizer may produce non-commanded movement under the action of aerodynamic external loads, thereby causing catastrophic failure. Therefore, the horizontal stabilizer trim actuator usually needs to be designed with a locking structure, which is used to lock the horizontal stabilizer trim actuator in time when the universal joint or ball screw fails to ensure failure safety.

[0004] When the horizontal stabilizer trim actuator fails, the existing locking structure may produce axial flutter due to changes in the direction of the aerodynamic external load. This phenomenon may cause the locking structure to be unable to effectively restrain the horizontal stabilizer, thereby posing a threat to flight safety. Summary of the invention

[0005] Embodiments of the present invention provide a locking structure and a horizontal stabilizer trim actuator, aiming to improve the reliability of the locking structure and the overall stability of the horizontal stabilizer trim actuator.

[0006] In order to solve the above technical problems, the embodiments of the present invention disclose the following technical solutions:

[0007] On the one hand, a locking structure is provided, which is applied to a horizontal stabilizer trim actuator, wherein the horizontal stabilizer trim actuator includes a rolling screw, and the locking structure includes:

[0008] The locking rod comprises a first rod and a second rod connected to each other, the rolling screw is a hollow structure, the first rod is used to be inserted into the rolling screw and fixedly connected to the rolling screw, and the second rod is used to pass through the rolling screw;

[0009] A joint, used to connect with the fuselage structure, comprising a limiting shell, the limiting shell having a limiting space, the limiting shell being sleeved on the second rod and slidably connected with the second rod, and the second rod being able to slide in the limiting space along the axial direction of the locking rod;

[0010] Among them, along the axial direction of the locking rod, a plurality of groups of limit grooves are arranged on the second rod at intervals, and safety positions are formed at the intervals between adjacent limit groove groups. A limit notch is arranged on the outer peripheral wall of the limit shell, and a limit block is arranged in the limit notch. When the second rod rotates, the projection of the limit block on the second rod overlaps with the safety position. When the second rod slides along the axial direction of the locking rod, the limit block is embedded in the limit groove group.

[0011] In addition to one or more of the features disclosed above, or as an alternative, along the axial direction of the locking rod, the second rod is provided with two groups of limit grooves at intervals, and a safety position is formed at the interval between the two groups of limit grooves. When the second rod rotates, the projection of the limit block on the second rod overlaps with the safety position.

[0012] In addition to or as an alternative to one or more of the features disclosed above, in the axial direction of the locking rod, the safety position has a first side and a second side, the first side faces away from the first rod, and the second side faces toward the first rod;

[0013] When the second rod moves along the axial direction of the locking rod toward a direction away from the limiting shell, the limiting block is embedded in the limiting groove group located on the first side;

[0014] When the second rod moves along the axial direction of the locking rod toward the direction close to the limiting shell, the limiting block is embedded in the limiting groove group located on the second side.

[0015] In addition to or as an alternative to one or more of the features disclosed above, the limit block is rotatably connected to the limit notch via a preload spring;

[0016] When the second rod moves along the axial direction of the locking rod toward a direction away from the limiting housing, the preload spring drives the limiting block to rotate so that the limiting block is embedded in the limiting groove group located on the first side;

[0017] When the second rod moves along the axial direction of the locking rod toward the direction close to the limiting housing, the preload spring drives the limiting block to rotate so that the limiting block is embedded in the limiting groove group located on the second side.

[0018] In addition to or as an alternative to one or more of the features disclosed above, the limiting groove group includes a plurality of limiting grooves, and the plurality of limiting grooves are spaced apart along the circumference of the second rod.

[0019] In addition to one or more of the features disclosed above, or as an alternative, along the circumference of the limit shell, a plurality of groups of limit notches are spaced apart on the outer circumferential wall of the limit shell, each group of the limit notches includes at least one or two limit notches, and each of the limit notches has a limit block.

[0020] In addition to one or more of the features disclosed above, or as an alternative, along the circumference of the limiting shell, two groups of limiting notches are spaced apart on the outer peripheral wall of the limiting shell, each group of the limiting notches includes two, and each of the limiting notches has a limiting block;

[0021] Along the radial direction of the limiting shell, the two groups of limiting notches are arranged opposite to each other.

[0022] In addition to or as an alternative to one or more of the features disclosed above, the joint further comprises a base, which is connected to a side of the limiting shell facing away from the first rod and closes the limiting space.

[0023] In addition to or as an alternative to one or more of the features disclosed above, a lug is protruding from a side of the base facing away from the limiting shell, and the lug is used to be connected to the fuselage structure.

[0024] In addition to one or more of the features disclosed above, or as an alternative, a limiting hole is opened on the side of the limiting shell facing the first rod, the second rod is inserted into the limiting hole, and the second rod has a first section with an outer diameter larger than an inner diameter of the limiting hole, and the first section is located in the limiting space.

[0025] On the other hand, a horizontal stabilizer trim actuator is provided, comprising a first connection structure, a second connection structure, a rolling screw and any of the above-disclosed locking structures, wherein the first connection structure is used to connect to the fuselage structure, the second connection structure is used to connect to the wing surface, the rod body of the rolling screw passes through the second connection structure, and one end is connected to the first connection structure, the locking rod is inserted into the rolling screw, and the joint of the locking structure is connected to the fuselage structure through the first connection structure;

[0026] When the horizontal stabilizer trim actuator works normally, the locking rod rotates with the rolling screw. When an abnormality occurs in the horizontal stabilizer trim actuator, the limit block limits the movement of the locking rod, and the locking rod limits the movement of the rolling screw.

[0027] One of the above technical solutions has the following advantages or beneficial effects: the application utilizes the cooperation of the limit groove group on the locking rod and the limit block on the limit shell, and when the horizontal stabilizer trim actuator fails structurally, it can effectively prevent the rolling screw from generating axial flutter, thereby preventing the horizontal stabilizer from generating non-command movement, thereby ensuring flight safety. Specifically, the locking rod is fixedly connected to the rolling screw through the first rod, and is slidably connected to the limit shell through the second rod. During the normal operation of the horizontal stabilizer trim actuator, the limit block is located in the safe position, the rolling screw can drive the locking rod to rotate, and the locking rod will not interfere with the normal operation of the horizontal stabilizer trim actuator. When the horizontal stabilizer trim actuator fails structurally, due to the change in the direction of the aerodynamic external load, the locking rod will be subjected to pressure or tension in the axial direction, thereby sliding along the axial direction. Regardless of whether the locking rod is subjected to compression or tension in its own axial direction, a relative displacement will occur between the locking rod and the limit shell. This relative displacement will cause the limit block installed on the limit housing to be embedded in the limit groove group located on the safety position side, thereby limiting the movement of the locking rod and effectively locking the horizontal stabilizer trim actuator. This design effectively improves the axial flutter problem of the locking rod caused by the change in the direction of the aerodynamic external load in the prior art, and improves the safety and reliability of the system. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] The technical solutions and other beneficial effects of the present invention will be made apparent by describing in detail the specific embodiments of the present invention in conjunction with the accompanying drawings.

[0029] Figure 1 This is a schematic diagram of a locking structure provided in an embodiment of the present application. Figure 1 ;

[0030] Figure 2 This is a schematic diagram of a locking structure provided in an embodiment of the present application. Figure 2 ;

[0031] Figure 3 This is a schematic diagram of a locking structure provided in an embodiment of the present application. Figure 3 ;

[0032] Figure 4 This is a schematic diagram of a locking structure provided in an embodiment of the present application. Figure 4 ;

[0033] Figure 5 This is a schematic diagram of a locking structure provided in an embodiment of the present application. Figure 5 ;

[0034] Figure 6 It is a structural schematic diagram of a horizontal stabilizer trim actuator provided in an embodiment of the present application.

[0035] Description of reference numerals:

[0036] 10. rolling screw; 11. first connecting structure; 12. second connecting structure;

[0037] 20, locking rod; 21, first rod; 22, second rod; 221, limit groove group; 2211, limit groove; 222, safety position; 223, first section;

[0038] 30. Joint; 31. Limiting shell; 311. Limiting notch; 312. Limiting hole; 313. Limiting block; 32. Base; 321. Ear. DETAILED DESCRIPTION

[0039] The technical solutions in the embodiments of the present application will be described clearly and completely below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present application.

[0040] The embodiment of the present invention discloses a locking structure, which is applied to a horizontal stabilizer trim actuator. The horizontal stabilizer trim actuator includes a rolling screw 10 (refer to Figure 6 ). Reference Figure 1 and Figure 2The locking structure includes a locking rod 20 and a joint 30. When the horizontal stabilizer trim actuator works normally, the locking rod 20 can rotate with the rolling screw 10. When the horizontal stabilizer trim actuator fails structurally, the joint 30 can limit the rotation and sliding of the locking rod 20, thereby limiting the movement of the rolling screw 10 to prevent the horizontal stabilizer trim actuator from driving the wing surface (horizontal stabilizer) to produce non-command movement. Specifically, the locking rod 20 has a first rod 21 and a second rod 22 connected to each other. The rolling screw 10 is a hollow structure. The first rod 21 is inserted into the rolling screw 10 and is fixedly connected to the rolling screw 10. The second rod 22 passes through the rolling screw 10. The joint 30 is used to connect to the fuselage structure, and includes a limit shell 31. The limit shell 31 has a limit space. The limit shell 31 is sleeved on the second rod 22 and is slidably connected to the second rod 22. The second rod 22 can slide along the axial direction of the locking rod 20 and rotate along the circumferential direction of the locking rod 20 in the limiting space. Among them, along the axial direction of the locking rod 20, the second rod 22 is provided with multiple groups of limiting groove groups 221 at intervals, and the intervals between adjacent limiting groove groups 221 form safety positions 222. A limiting notch 311 is provided on the outer peripheral wall of the limiting shell 31, and a limiting block 313 is provided in the limiting notch 311. When the second rod 22 rotates, the projection of the limiting block 313 on the second rod 22 overlaps with the safety position 222, and when the second rod 22 slides along the axial direction of the locking rod 20, the limiting block 313 is embedded in the limiting groove group 221. It should be noted that the first rod 21 and the second rod 22 are integrally formed to form the locking rod 20, so the axes of the first rod 21, the second rod 22 and the locking rod 20 formed by the two coincide.

[0041] The present application cooperates with the limit groove group 221 on the locking rod 20 and the limit block 313 on the limit shell 31 to effectively prevent the rolling screw 10 from generating axial flutter (axial flutter specifically refers to: the rolling screw 10 slides back and forth along its own axial direction) when the horizontal stabilizer trim actuator fails structurally, thereby preventing the horizontal stabilizer from generating non-command movement, thereby ensuring flight safety. Specifically, the locking rod 20 is fixedly connected to the rolling screw 10 through the first rod 21, and is slidably connected to the limit shell 31 through the second rod 22. During the normal operation of the horizontal stabilizer trim actuator, the limit block 313 is located in the safety position 222, the rolling screw 10 can drive the locking rod 20 to rotate, and the locking rod 20 will not interfere with the normal operation of the horizontal stabilizer trim actuator. When the horizontal stabilizer trim actuator fails structurally, due to the change in the direction of the aerodynamic external load, the locking rod 20 will be subjected to pressure or tension in the axial direction, thereby sliding in the axial direction. Regardless of whether the locking rod 20 is compressed or pulled in its own axial direction, a relative displacement will occur between the locking rod 20 and the limiting shell 31. This relative displacement will cause the limiting block 313 installed on the limiting shell 31 to be embedded in the limiting groove group 221 located on the side of the safety position 222, thereby limiting the movement of the locking rod 20 and effectively locking the horizontal stabilizer trim actuator. Such a design effectively improves the axial flutter problem of the horizontal stabilizer trim actuator caused by the change in the direction of the aerodynamic external load in the prior art, and improves the safety and reliability of the system. At the same time, the present application effectively locks the horizontal stabilizer trim actuator through the coordination of the limiting block 313 and the limiting groove group 221, and the processing difficulty is low. Compared with the prior art of braking and resetting the locking rod by the reset rod through the locking rod, the present application reduces the overall weight of the locking structure and reduces the manufacturing cost of the locking structure.

[0042] In the technical solution disclosed in the present application, along the axial direction of the locking rod 20, multiple groups of limit grooves 221 are arranged on the second rod 22 at intervals, and safety positions 222 are formed at intervals between adjacent limit grooves 221. In order to more clearly illustrate the specific implementation of multiple groups of limit grooves 221, the solution will be explained in detail below through two preferred embodiments.

[0043] Preferably, the embodiment 1 of the plurality of limit groove groups 221: Figure 1 , along the axial direction of the locking rod 20, the second rod 22 is provided with two groups of limit grooves 221 at intervals, and the interval between the two groups of limit grooves 221 forms a safety position 222. In other words, when the second rod 22 is provided with two groups of limit grooves 221 at intervals, only one safety position 222 is formed, and the outer peripheral wall of the second rod 22 between the two groups of limit grooves 221 is the safety position 222. Figure 1 and Figure 3When the horizontal stabilizer trim actuator is working normally, the locking rod 20 rotates driven by the rolling screw 10 (that is, the second rod 22 rotates at this time), and the projection of the limit block 313 on the second rod 22 overlaps with the projection of the safety position 222. The limit block 313 will not interfere with the rotation of the second rod 22. When the horizontal stabilizer trim actuator fails structurally, the direction of the aerodynamic external load changes, and the locking rod 20 will be subjected to pressure or tension in the axial direction, thereby sliding along its own axial direction. Specifically, in the axial direction of the locking rod 20, the safety position 222 has a first side and a second side, the first side is away from the first rod 21, and the second side is toward the first rod 21. Refer to Figure 1 and Figure 4 When the locking rod 20 is subjected to tension in the axial direction, the locking rod 20 slides along its own axial direction toward the direction away from the limiting shell 31. At this time, the limiting shell 31 does not slide, that is, the limiting block 313 does not slide either. After sufficient relative displacement occurs between the second rod 22 and the limiting shell 31, the limiting block 313 is embedded in the limiting groove group 221 located on the first side of the safety position 222 to limit the movement of the locking rod 20. When the locking rod 20 is subjected to pressure in the axial direction, the locking rod 20 slides along its own axial direction toward the direction close to the limiting shell 31. At this time, the limiting shell 31 does not slide, that is, the limiting block 313 does not slide either. After sufficient relative displacement occurs between the second rod 22 and the limiting shell 31, the limiting block 313 is embedded in the limiting groove group 221 located on the second side of the safety position 222 to limit the movement of the locking rod 20.

[0044] Preferably, the second embodiment of the plurality of limit groove groups 221: Figure 5 , along the axial direction of the locking rod 20, the second rod 22 is provided with three groups of limit grooves 221 at intervals, and the intervals between two adjacent groups of limit grooves 221 form a safety position 222. In other words, when the second rod 22 is provided with three groups of limit grooves 221, two safety positions 222 are formed, and the outer peripheral wall of the second rod 22 between two adjacent groups of limit grooves 221 is the safety position 222. Correspondingly, the limit housing 31 is provided with limit notches 311 at intervals along the axial direction of the locking rod 20, and each limit notch 311 has a limit block 313. The limit notches 311 provided at intervals along the axial direction of the locking rod 20 correspond to the safety positions 222. When the horizontal stabilizer trim actuator works normally, the locking rod 20 rotates under the drive of the rolling screw 10 (that is, the second rod 22 rotates at this time), and the projection of the limit block 313 on the second rod 22 overlaps with the projection of the corresponding safety position 222. The stopper 313 does not interfere with the rotation of the second rod 22. When the horizontal stabilizer trim actuator fails, the direction of the aerodynamic external load changes, and the locking rod 20 is subjected to pressure or tension in the axial direction, thereby sliding in the axial direction. In the axial direction of the locking rod 20, each safety position 222 has a first side and a second side, the first side is away from the first rod 21, and the second side is toward the first rod 21. Figure 4 and Figure 5 When the locking rod 20 is subjected to tension in the axial direction, the locking rod 20 slides along its own axial direction toward the direction away from the limiting shell 31. At this time, the limiting shell 31 remains stationary, that is, the limiting block 313 does not slide. After sufficient relative displacement occurs between the second rod 22 and the limiting shell 31, the limiting block 313 is located on the first side of the corresponding safety position 222 and is embedded in the limiting groove group 221 located on this side to limit the movement of the locking rod 20. When the locking rod 20 is subjected to pressure in the axial direction, the locking rod 20 slides along its own axial direction toward the direction close to the limiting shell 31. At this time, the limiting shell 31 remains stationary, that is, the limiting block 313 does not slide. After sufficient relative displacement occurs between the second rod 22 and the limiting shell 31, the limiting block 313 is located on the second side of the corresponding safety position 222 and is embedded in the limiting groove group 221 located on this side to limit the movement of the locking rod 20.

[0045] In the second embodiment of the multiple groups of limit groove groups 221 disclosed in the present application, three groups of limit groove groups 221 are introduced. When the horizontal stabilizer trim actuator suffers structural failure, this embodiment can limit the movement of the locking rod 20 at two different positions in the axial direction of the second rod 22. This double limit design can further effectively improve the axial flutter problem of the horizontal stabilizer trim actuator in the prior art caused by the change in the direction of the aerodynamic external load, thereby further improving the safety and reliability of the system.

[0046] It should be noted that, although the number of the plurality of groups of limit grooves 221 spaced apart on the second rod 22 is preferably two or three groups, in practical applications, more groups of limit grooves 221 spaced apart along the axial direction of the second rod 22 can be provided with reference to the first and second embodiments of the plurality of groups of limit grooves 221 disclosed in the present application, according to the size of the horizontal stabilizer trim actuator. The distance between two adjacent groups of limit grooves 221 is also designed according to the size of the horizontal stabilizer trim actuator.

[0047] Further, in some embodiments of the locking structure, the limit block 313 is rotatably connected to the limit notch 311 via the mounting shaft. Specifically, the mounting shaft has a preload spring, and the axial direction of the mounting shaft is arranged along the axial direction of the locking rod 20 (specifically, refer to Figure 2 and Figure 3, the through hole opened on each limit block 313 along the axial direction of the locking rod 20 is used for the installation shaft to pass through. ), so as to apply a preload force to the limit block 313 along the radial direction of the locking rod 20. When the second rod 22 moves along the axial direction of the locking rod 20 toward the direction away from the limit housing 31, the preload spring releases the preload force and drives the installation shaft to rotate, and the installation shaft drives the limit block 313 to rotate so that the limit block 313 is embedded in the limit groove group 221 located on the first side. When the second rod 22 moves along the axial direction of the locking rod 20 toward the direction close to the limit housing 31, the preload spring releases the preload force and drives the installation shaft to rotate, and the installation shaft drives the limit block 313 to rotate so that the limit block 313 is embedded in the limit groove group 221 located on the second side.

[0048] It is worth mentioning that after the horizontal stabilizer trim actuator has completed the relevant inspection and maintenance, the preload force can be reapplied by pressing the limit block 313, and the limit block 313 can be separated from the limit groove group 221, so as to allow the second rod 22 to slide along the axial direction of the locking rod 20 and reset. Specifically, the limit groove group 221 includes the limit groove 2211. After the horizontal stabilizer trim actuator fails in structure, the second rod 22 and the limit housing 31 have sufficient relative displacement, and the state of the limit block 313 will change from Figure 3 becomes Figure 4 The stop block 313 is driven by the preload spring to rotate around the axial direction of the installation shaft. In the circumferential direction of the second rod 22, the end of the stop block 313 away from the installation shaft enters the stop groove 2211, and the end face of the stop block 313 abuts against the groove wall of the stop groove 2211. When the locking rod 20 is reset by pressing the stop block 313, the state of the stop block 313 changes from Figure 4 becomes Figure 3 The limit block 313 will rotate in the opposite direction around the axial direction of the installation shaft, and the end of the limit block 313 away from the installation shaft will leave the limit groove 2211, the second rod 22 will be reset, and the projection of the limit block 313 and the safety position 222 on the second rod 22 will resume the overlapping state.

[0049] Furthermore, in actual application, the locking rod 20 rotates with the rolling screw 10. When the horizontal stabilizer trim actuator fails structurally, in order to ensure that the limit block 313 can be timely embedded in the limit groove group 221 to limit the movement of the locking rod 20. In some embodiments of the locking structure, each limit groove group 221 includes a plurality of limit grooves 2211, and the plurality of limit grooves 2211 are arranged at intervals along the circumference of the second rod 22. In this way, no matter how the locking rod 20 rotates, it can be ensured that when the horizontal stabilizer trim actuator fails structurally, the limit block 313 has a matching limit groove 2211 on the side facing the second rod 22, thereby ensuring that the limit block 313 can be smoothly embedded in the limit groove 2211, thereby effectively limiting the movement of the locking rod 20.

[0050] Furthermore, in some embodiments of the locking structure, along the circumference of the limiting shell 31, a plurality of groups of limiting notches 311 are spaced apart on the outer circumferential wall of the limiting shell 31, each group of limiting notches 311 includes at least one or two limiting notches 311, and each limiting notch 311 has a limiting block 313. In this way, multiple limiting positions can be added on the circumference of the second rod 22 to effectively limit the rotation of the second rod. Preferably, referring to Figure 3 and Figure 4 , two groups of limiting notches 311 are arranged on the outer peripheral wall of the limiting shell 31 at intervals along the circumference of the limiting shell 31, and the two groups of limiting notches 311 are arranged opposite to each other along the radial direction of the limiting shell 31. Each group of limiting notches 311 includes two, and each limiting notch 311 has a limiting block 313. With such arrangement, after the horizontal stabilizer trim actuator completes the relevant inspection and maintenance, it is convenient to press the limiting block 313 so that the limiting block 313 is away from the limiting groove 2211, so as to reset the second rod 22. Similarly, in some embodiments, if the number of limiting notches 311 opened along the circumference of the limiting shell 31 is an even number greater than two groups, they can be arranged to be arranged opposite to each other in pairs.

[0051] In some embodiments of the locking structure, a limiting hole 312 is provided on a side of the limiting shell 31 facing the first rod 21, and the second rod 22 is inserted into the limiting hole 312. The second rod 22 has a first section 223 whose outer diameter is larger than the inner diameter of the limiting hole 312, and the first section 223 is located in the limiting space and can slide and rotate in the limiting space. In this way, when the horizontal stabilizer trim actuator fails in structure and the second rod 22 is subjected to tension in the axial direction and moves in a direction away from the limiting shell 31, it can be ensured that the second rod 22 will not fall out of the limiting shell 31. Preferably, in some embodiments, the limiting groove group 221 disclosed above is provided on the outer peripheral wall of the first section 223. It should be noted that when the horizontal stabilizer trim actuator works normally, there is a gap between the end surface of the first section 223 facing one end of the first rod 21 and the inner wall of the limiting shell 31 facing the first rod 21, and the first section 223 will not interfere with the rotation of the locking rod 20.

[0052] In some embodiments of the locking structure, the joint 30 further includes a base 32, which is connected to the side of the limiting shell 31 away from the first rod 21 and closes the limiting space. In this way, when the horizontal stabilizer trim actuator fails in structure and the second rod 22 is subjected to pressure in the axial direction and moves toward the limiting shell 31, it is ensured that the second rod 22 will not fall out from the side of the limiting shell 31 away from the first rod 21. It should be noted that when the horizontal stabilizer trim actuator works normally, there is a gap between the end surface of the end of the second rod 22 facing the base 32 and the wall surface of the base 32 facing the limiting shell 31, and the base 32 will not interfere with the rotation of the locking rod 20.

[0053] Furthermore, in some embodiments, a lug 321 is protruding from one side of the base 32 away from the limiting shell 31 , and the lug 321 can facilitate the connection between the locking structure and the fuselage structure.

[0054] The present application also provides a horizontal stabilizer trim actuator, referring to Figure 6 The horizontal stabilizer trim actuator comprises: a first connecting structure 11, a second connecting structure 12, a rolling screw 10 and any locking structure disclosed above (it should be noted that in Figure 6 The locking structure is blocked by the rolling screw 10 and the first connecting structure 11 and is not shown). The first connecting structure 11 is used to connect to the fuselage structure, and the second connecting structure 12 is used to connect to the wing surface (i.e., the horizontal stabilizer). The rod body of the rolling screw 10 passes through the second connecting structure 12, and one end is connected to the first connecting structure 11. The rolling screw 10 is a hollow structure, and the locking rod 20 is inserted into the rolling screw 10. The joint 30 of the locking structure is connected to the fuselage structure through the first connecting structure 11. When the horizontal stabilizer trim actuator works normally, the locking rod 20 rotates with the rolling screw 10. When an abnormality occurs in the horizontal stabilizer trim actuator, the limit block 313 limits the movement of the locking rod 20, and the locking rod 20 limits the movement of the rolling screw 10.

[0055] In the description of this application, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more features. In the description of this application, the meaning of "plurality" is two or more, unless otherwise clearly and specifically defined.

[0056] In the above embodiments, the description of each embodiment has its own emphasis. For parts that are not described in detail in a certain embodiment, reference can be made to the relevant descriptions of other embodiments.

[0057] The embodiments, implementation methods and related technical features of the present application can be combined and replaced with each other without conflict.

[0058] The above are only preferred embodiments of the present application and do not constitute any form of limitation to the present application. However, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present application without departing from the content of the technical solution of the present application are still within the scope of the technical solution of the present application.

Claims

1. A locking structure, characterized in that: Applicable to a horizontal stabilizer trim actuator, the horizontal stabilizer trim actuator comprises a rolling screw (10), and the locking structure comprises: The locking rod (20) comprises a first rod (21) and a second rod (22) connected to each other, the rolling screw (10) being a hollow structure, the first rod (21) being used to be inserted into the rolling screw (10) and being fixedly connected to the rolling screw (10), and the second rod (22) being used to pass through the rolling screw (10); The joint (30) is used to be connected to the fuselage structure, and comprises a limiting shell (31), wherein the limiting shell (31) has a limiting space, the limiting shell (31) is sleeved on the second rod (22), and is slidably connected to the second rod (22), and the second rod (22) can slide in the limiting space along the axial direction of the locking rod (20); Wherein, along the axial direction of the locking rod (20), a plurality of groups of limiting groove groups (221) are arranged on the second rod (22) at intervals, and safety positions (222) are formed at intervals between adjacent limiting groove groups (221); a limiting notch (311) is arranged on the outer peripheral wall of the limiting shell (31), and a limiting block (313) is arranged in the limiting notch (311); when the second rod (22) rotates, the projection of the limiting block (313) on the second rod (22) overlaps with the projection of the safety position (222); when the second rod (22) slides along the axial direction of the locking rod (20), the limiting block (313) is embedded in the limiting groove group (221).

2. The locking structure according to claim 1, characterized in that: Along the axial direction of the locking rod (20), the second rod (22) is provided with two groups of limit groove groups (221) at intervals, and a safety position (222) is formed at the interval between the two groups of limit groove groups (221). When the second rod (22) rotates, the projection of the limit block (313) on the second rod (22) overlaps with the projection of the safety position (222).

3. The locking structure according to claim 1, characterized in that: In the axial direction of the locking rod (20), the safety position (222) has a first side and a second side, the first side faces away from the first rod (21), and the second side faces the first rod (21); When the second rod (22) moves along the axial direction of the locking rod (20) in a direction away from the limiting shell (31), the limiting block (313) is embedded in the limiting groove group (221) located on the first side; When the second rod (22) moves along the axial direction of the locking rod (20) toward the direction approaching the limiting shell (31), the limiting block (313) is embedded in the limiting groove group (221) located on the second side.

4. The locking structure according to claim 3, characterized in that: The limiting block (313) is rotatably connected to the limiting notch (311) via a mounting shaft, and a preload spring is provided on the mounting shaft; When the second rod (22) moves along the axial direction of the locking rod (20) in a direction away from the limiting shell (31), the preload spring drives the installation shaft to rotate, and the installation shaft drives the limiting block (313) to rotate so that the limiting block (313) is embedded in the limiting groove group (221) located on the first side; When the second rod (22) moves along the axial direction of the locking rod (20) toward the limit shell (31), the preload spring drives the installation shaft to rotate, and the installation shaft drives the limit block (313) to rotate so that the limit block (313) is embedded in the limit groove group (221) located on the second side.

5. The locking structure according to claim 1, characterized in that: The limiting groove group (221) comprises a plurality of limiting grooves (2211), and the plurality of limiting grooves (2211) are arranged at intervals along the circumference of the second rod (22).

6. The locking structure according to claim 1, characterized in that: Along the circumference of the limiting shell (31), a plurality of groups of limiting notches (311) are arranged at intervals on the outer peripheral wall of the limiting shell (31), each group of the limiting notches (311) includes at least one or two limiting notches (311), and each limiting notch (311) has a limiting block (313).

7. The locking structure according to claim 1, characterized in that: Along the circumferential direction of the limiting shell (31), two groups of limiting notches (311) are spaced apart on the outer peripheral wall of the limiting shell (31), each group of the limiting notches (311) comprises two, and each of the limiting notches (311) has a limiting block (313); Along the radial direction of the limiting shell (31), the two groups of limiting notches (311) are arranged opposite to each other.

8. The locking structure according to claim 1, characterized in that: The joint (30) further comprises a base (32), wherein the base (32) is connected to a side of the limiting shell (31) away from the first rod (21) and closes the limiting space.

9. The locking structure according to claim 8, characterized in that: A lug (321) is protrudingly provided on a side of the base (32) facing away from the limiting shell (31), and the lug (321) is used to be connected to the fuselage structure.

10. The locking structure according to claim 1, characterized in that: The limiting shell (31) is provided with a limiting hole (312) on one side facing the first rod (21); the second rod (22) is inserted into the limiting hole (312); the second rod (22) has a first section (223) whose outer diameter is greater than the inner diameter of the limiting hole (312); and the first section (223) is located in the limiting space.

11. A horizontal stabilizer trim actuator, characterized in that: The invention comprises a first connection structure (11), a second connection structure (12), a rolling screw (10) and any one of the locking structures disclosed in claims 1 to 10, wherein the first connection structure (11) is used to connect to the fuselage structure, the second connection structure (12) is used to connect to the wing surface, the rod body of the rolling screw (10) passes through the second connection structure (12), and one end is connected to the first connection structure (11); the rolling screw (10) is a hollow structure, the locking rod (20) is inserted into the rolling screw (10), and the joint (30) of the locking structure is connected to the fuselage structure through the first connection structure (11); When the horizontal stabilizer trim actuator works normally, the locking rod (20) rotates with the rolling screw (10); when an abnormality occurs in the horizontal stabilizer trim actuator, the limit block (313) limits the movement of the locking rod (20), and the locking rod (20) limits the movement of the rolling screw (10).

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