Locking structure and horizontal stabilizer trim actuator

Abstract

The embodiment of the present application discloses a locking structure and a horizontal stabilizer trimming actuator, wherein the locking structure is applied to the horizontal stabilizer trimming actuator, and the horizontal stabilizer trimming actuator comprises a hollow rolling screw. The locking structure comprises a locking rod and a joint. The locking rod has a first rod and a second rod connected with each other, the first rod is used for being arranged in the rolling screw and fixedly connected with the rolling screw, and the second rod is used for being arranged out of the rolling screw. The joint comprises a limiting shell, and the limiting shell is sleeved on the second rod and slidably connected with the second rod. Wherein, a plurality of groups of limiting groove groups are arranged on the second rod in the axial direction of the locking rod, a safety position is formed at intervals between adjacent limiting groove groups, a limiting gap is formed on the outer peripheral wall of the limiting shell, the limiting gap is provided with a limiting block, when the second rod rotates, the projection of the limiting block on the second rod overlaps with the safety position, and when the second rod slides in the axial direction of the locking rod, the limiting block is embedded in the limiting groove group.

Description

TECHNICAL FIELD

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

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

[0003] The current horizontal stabilizer trim actuator (HSTA) generally transmits load to the fuselage structure and the airfoil through a universal joint and a ball screw, if these structures (universal joint or ball screw) fail, under the action of aerodynamic external load, it may cause the horizontal stabilizer to move non-instructively, thus causing a 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] The existing locking structure may produce axial chatter when the horizontal stabilizer trim actuator fails, which may cause the locking structure to be unable to effectively constrain the horizontal stabilizer, thus threatening flight safety. SUMMARY

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

[0006] To solve the above technical problems, embodiments of the present application disclose the following technical solutions:

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

[0008] A locking rod having a first rod and a second rod connected, the rolling screw being a hollow structure, the first rod being used to pass through the rolling screw and being fixedly connected with the rolling screw, and the second rod being used to pass out of the rolling screw;

[0009] A joint for connecting with a fuselage structure, comprising a limiting shell having a limiting space, the limiting shell being sleeved on the second rod and being in sliding connection with the second rod, the second rod being capable of sliding in the limiting space along the axial direction of the locking rod;

[0010] Wherein, along the axial direction of the locking rod, a plurality of sets of limiting grooves are spaced apart on the second rod, and a safety position is formed at the interval between adjacent sets of limiting grooves, a limiting notch is formed on the outer peripheral wall of the limiting shell, and a limiting block is arranged in the limiting notch, when the second rod rotates, the projection of the limiting block on the second rod overlaps the safety position, and when the second rod slides along the axial direction of the locking rod, the limiting block is embedded in the limiting groove set.

[0011] In addition to one or more features disclosed above, or as an alternative, along the axial direction of the locking rod, two sets of limiting grooves are spaced apart on the second rod, and a safety position is formed at the interval between the two sets of limiting grooves, and when the second rod rotates, the projection of the limiting block on the second rod overlaps the safety position.

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

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

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

[0015] In addition to one or more features disclosed above, or as an alternative, the limiting block is rotatably connected with the limiting notch through a pre-tightening spring;

[0016] When the second rod moves along the axial direction of the locking rod towards the direction away from the limiting shell, the pre-tightening spring drives the limiting block to rotate so that the limiting block is embedded in the limiting groove set on the first side;

[0017] When the second rod moves along the axial direction of the locking rod towards the direction close to the limiting shell, the pre-tightening spring drives the limiting block to rotate so that the limiting block is embedded in the limiting groove set on the second side.

[0018] In addition to one or more of the above disclosed features, or alternatively, the plurality of limiting grooves are spaced along a circumference of the second rod.

[0019] In addition to one or more of the above disclosed features, or alternatively, a plurality of sets of limiting notches are spaced along a circumference of the limiting shell, each set of limiting notches includes at least one or two limiting notches, and each limiting notch has a limiting block.

[0020] In addition to one or more of the above disclosed features, or alternatively, two sets of limiting notches are spaced along a circumference of the limiting shell, each set of limiting notches includes two limiting notches, and each limiting notch has a limiting block.

[0021] The two sets of limiting notches are opposite to each other along a radial direction of the limiting shell.

[0022] In addition to one or more of the above disclosed features, or alternatively, the joint further includes a base connected to a side of the limiting shell away from the first rod and enclosing the limiting space.

[0023] In addition to one or more of the above disclosed features, or alternatively, the base protrudes an ear from a side of the base away from the limiting shell, and the ear is used to connect with the fuselage structure.

[0024] In addition to one or more of the above disclosed features, or alternatively, the limiting shell is provided with a limiting hole on a side of the limiting shell facing the first rod, the second rod is arranged in the limiting hole, and the second rod has a first section with an outer diameter greater than an inner diameter of the limiting hole, and the first section is located in the limiting space.

[0025] In another aspect, a horizontal stabilizer trim actuator is provided, which includes a first connecting structure, a second connecting structure, a rolling screw, and any of the above disclosed locking structures, the first connecting structure is used to connect with the fuselage structure, the second connecting structure is used to connect with a wing surface, a rod of the rolling screw penetrates through the second connecting structure and is connected with the first connecting structure at one end, the locking rod is arranged in the rolling screw, and the joint of the locking structure is connected with the fuselage structure through the first connecting structure.

[0026] When the horizontal stabilizer trim actuator is working normally, the locking rod rotates with the rolling screw, when the horizontal stabilizer trim actuator is abnormal, the limiting 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 limiting groove set on the locking rod and the limiting block on the limiting shell to effectively prevent the axial flutter of the rolling screw when the structure of the horizontal stabilizer trim actuator fails, thereby preventing the horizontal stabilizer from moving non-instructively, and ensuring flight safety. Specifically, the locking rod is fixedly connected with the rolling screw through a first rod and is slidingly connected with the limiting shell through a second rod. During normal operation of the horizontal stabilizer trim actuator, the limiting block is in a safe position, the rolling screw can drive the locking rod to rotate, and the locking rod does not interfere with the normal operation of the horizontal stabilizer trim actuator. When the structure of the horizontal stabilizer trim actuator fails, the locking rod will be subjected to pressure or tension in the axial direction due to the change in the direction of the aerodynamic external load, and thus will slide in the axial direction. Regardless of whether the locking rod is subjected to pressure or tension in the axial direction, relative displacement will occur between the locking rod and the limiting shell. This relative displacement will cause the limiting block mounted on the limiting shell to be embedded into the limiting groove set on the safe position side, thereby limiting the movement of the locking rod and effectively locking the horizontal stabilizer trim actuator. In this way, the axial flutter of the locking rod caused by the change in the direction of the aerodynamic external load in the prior art is effectively improved, and the safety and reliability of the system are improved. BRIEF DESCRIPTION OF DRAWINGS

[0028] The technical solutions of the application and other beneficial effects will become apparent from the following detailed description of the specific embodiments of the application, combined with the accompanying drawings.

[0029] Figure 1 is a structure diagram of a locking structure provided by an embodiment of the application Figure 1 ;

[0030] Figure 2 is a structure diagram of a locking structure provided by an embodiment of the application Figure 2 ;

[0031] Figure 3 is a structure diagram of a locking structure provided by an embodiment of the application Figure 3 ;

[0032] Figure 4 is a structure diagram of a locking structure provided by an embodiment of the application Figure 4 ;

[0033] Figure 5 is a structure diagram of a locking structure provided by an embodiment of the application Figure 5 ;

[0034] Figure 6 is a structure diagram of a horizontal stabilizer trim actuator provided by an embodiment of the application.

[0035] BRIEF DESCRIPTION OF DRAWINGS

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

[0037] 20, locking rod; 21, first rod; 22, second rod; 221, limiting groove set; 2211, limiting 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 clearly and completely described below with reference to 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 the embodiments. Based on the embodiments in the present application, all other embodiments obtained by a person skilled in the art without creative labor fall within the protection scope of the present application.

[0040] The embodiments of the present application disclose a locking structure applied to a horizontal stabilizer trimming actuator, wherein the horizontal stabilizer trimming actuator comprises a rolling screw 10 (refer to Figure 6 ) and a rolling nut 20 (refer to Figure 1 and Figure 2The locking structure comprises a locking rod 20 and a joint 30. When the horizontal stabilizer trim actuator is working normally, the locking rod 20 can rotate with the rolling screw 10. When the horizontal stabilizer trim actuator fails, the joint 30 can limit the rotation and sliding of the locking rod 20, and further limit the movement of the rolling screw 10, so as to avoid the non-instructive movement of the horizontal stabilizer trim actuator driving the airfoil (horizontal stabilizer). Specifically, the locking rod 20 has a first rod 21 and a second rod 22 connected with each other. The rolling screw 10 is a hollow structure. The first rod 21 is arranged in the rolling screw 10 and is fixedly connected with the rolling screw 10. The second rod 22 penetrates out of the rolling screw 10. The joint 30 is used to be connected with the fuselage structure and comprises a limiting shell 31 having a limiting space. The limiting shell 31 is sleeved on the second rod 22 and is slidably connected with 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. Wherein, a plurality of limiting groove groups 221 are arranged on the second rod 22 in the axial direction of the locking rod 20. The adjacent limiting groove groups 221 are spaced apart and form safety positions 222. A limiting notch 311 is formed on the outer circumferential wall of the limiting shell 31, and the limiting notch 311 has a limiting block 313. When the second rod 22 rotates, the projection of the limiting block 313 on the second rod 22 overlaps with 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. It should be noted that the first rod 21 and the second rod 22 are integrally formed and jointly constitute the locking rod 20. Therefore, the axes of the first rod 21, the second rod 22 and the locking rod 20 formed by the first rod 21 and the second rod 22 coincide.

[0041] The application cooperates the limiting groove group 221 on the locking rod 20 and the limiting block 313 on the limiting shell 31 to effectively prevent the rolling screw 10 from generating axial flutter (the axial flutter specifically refers to the rolling screw 10 sliding back and forth along the axial direction of itself) when the horizontal stabilizer trim actuator fails, and further prevent the horizontal stabilizer from generating non-instructional movement, thereby ensuring flight safety. Specifically, the locking rod 20 is fixedly connected with the rolling screw 10 through the first rod 21 and is slidingly connected with the limiting shell 31 through the second rod 22. During normal operation of the horizontal stabilizer trim actuator, the limiting block 313 is located at the safe position 222, the rolling screw 10 can drive the locking rod 20 to rotate, and the locking rod 20 does not interfere with the normal operation of the horizontal stabilizer trim actuator. When the horizontal stabilizer trim actuator fails, the locking rod 20 will be subjected to pressure or tension in the axial direction due to the change of the direction of the aerodynamic external load, thereby sliding in the axial direction. Regardless of whether the locking rod 20 is subjected to pressure or tension in the axial direction, relative displacement will be generated between the locking rod 20 and the limiting shell 31, which will cause the limiting block 313 mounted on the limiting shell 31 to be embedded in the limiting groove group 221 located on one side of the safe position 222, thereby limiting the movement of the locking rod 20 and effectively locking the horizontal stabilizer trim actuator. In this way, the axial flutter problem of the horizontal stabilizer trim actuator caused by the change of the direction of the aerodynamic external load in the prior art is effectively improved, and the safety and reliability of the system are improved. Meanwhile, the application effectively locks the horizontal stabilizer trim actuator through the cooperation of the limiting block 313 and the limiting groove group 221, which has low processing difficulty and reduces the overall weight and manufacturing cost of the locking structure compared with the prior art of using the reset rod penetrating the locking rod to brake and reset the locking rod.

[0042] In the technical solution disclosed in the application, a plurality of limiting groove groups 221 are spaced apart on the second rod 22 in the axial direction of the locking rod 20, and a safe position 222 is formed at the interval between adjacent limiting groove groups 221. In order to more clearly explain the specific implementation mode of the plurality of limiting groove groups 221, the following will explain this solution through two preferred embodiments.

[0043] Preferably, the first embodiment of the plurality of limiting groove groups 221 is as follows: Figure 1 In the axial direction of the locking rod 20, two limiting groove groups 221 are spaced apart on the second rod 22, and a safe position 222 is formed at the interval between the two limiting groove groups 221. In other words, when two limiting groove groups 221 are spaced apart on the second rod 22, only one safe position 222 will be formed, and the outer peripheral wall of the second rod 22 between the two limiting groove groups 221 is the safe position 222. Referring to Figure 1 and Figure 3In the normal working condition of the horizontal stabilizer trim actuator, the locking rod 20 rotates under the driving of the rolling screw 10 (i.e. the second rod 22 rotates at this time), the projection of the limiting block 313 on the second rod 22 overlaps the projection of the safety position 222. The limiting block 313 does not interfere with the rotation of the second rod 22. In the structural failure of the horizontal stabilizer trim actuator, the change of the direction of the aerodynamic external load, the locking rod 20 will be subjected to pressure or tension in the axial direction, thereby sliding along the 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 towards the first rod 21. Referring 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 the axial direction of itself towards the direction away from the limiting shell 31, at this time, the limiting shell 31 does not slide, i.e. the limiting block 313 also does not slide, after the relative displacement between the second rod 22 and the limiting shell 31 is sufficient, the limiting block 313 is embedded in the limiting groove group 221 located on the first side of the safety position 222, thereby limiting 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 the axial direction of itself towards the direction close to the limiting shell 31, at this time, the limiting shell 31 does not slide, i.e. the limiting block 313 also does not slide, after the relative displacement between the second rod 22 and the limiting shell 31 is sufficient, the limiting block 313 is embedded in the limiting groove group 221 located on the second side of the safety position 222, thereby limiting the movement of the locking rod 20.

[0044] Preferably, the second embodiment of the plurality of limiting groove groups 221: referring to Figure 5 , along the axial direction of the locking rod 20, the second rod 22 is spaced apart to be provided with three groups of limiting groove groups 221, and the interval between the adjacent two groups of limiting groove groups 221 forms a safety position 222. In other words, when the second rod 22 is provided with three groups of limiting groove groups 221, two safety positions 222 will be formed, and the outer peripheral wall of the second rod 22 between the adjacent two groups of limiting groove groups 221 is the safety position 222. Correspondingly, the limiting shell 31 is spaced apart to be provided with limiting notches 311 along the axial direction of the locking rod 20, and each limiting notch 311 is provided with a limiting block 313. The limiting notches 311 spaced apart along the axial direction of the locking rod 20 correspond to the safety positions 222, in the normal working condition of the horizontal stabilizer trim actuator, the locking rod 20 rotates under the driving of the rolling screw 10 (i.e. the second rod 22 rotates at this time), the projection of the limiting block 313 on the second rod 22 overlaps the projection of the corresponding safety position 222. And the limiting block 313 does not interfere with the rotation of the second rod 22. In the structural failure of the horizontal stabilizer trim actuator, the change of the direction of the aerodynamic external load, the locking rod 20 will be subjected to pressure or tension in the axial direction, thereby sliding along 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 towards the first rod 21. Referring to Figure 4 andFigure 5 When the locking rod 20 is subjected to a pulling force in the axial direction, the locking rod 20 slides along its own axial direction away from the limiting shell 31, at this time, the limiting shell 31 remains stationary, that is, the limiting block 313 also does not slide. After sufficient relative displacement is generated 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 the side to limit the movement of the locking rod 20. When the locking rod 20 is subjected to a pressure in the axial direction, the locking rod 20 slides along its own axial direction towards the limiting shell 31, at this time, the limiting shell 31 remains stationary, that is, the limiting block 313 also does not slide. After sufficient relative displacement is generated 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 the side to limit the movement of the locking rod 20.

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

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

[0047] Further, in some embodiments of the locking structure, the limiting block 313 is rotationally connected with the limiting gap 311 through a mounting shaft. Specifically, the mounting shaft has a pre-tightening spring thereon, 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 3Each limiting block 313 is provided with a through hole along the axial direction of the locking rod 20 for the installation shaft to pass through. A pre-tightening spring is arranged between the limiting block 313 and the limiting shell 31, and the pre-tightening spring is arranged to apply a pre-tightening force to the limiting block 313 in the radial direction of the locking rod 20. When the second rod 22 moves in the axial direction of the locking rod 20 away from the limiting shell 31, the pre-tightening spring releases the pre-tightening force and 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 on the first side. When the second rod 22 moves in the axial direction of the locking rod 20 towards the limiting shell 31, the pre-tightening spring releases the pre-tightening force and 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 on the second side.

[0048] It is worth mentioning that after the related maintenance of the horizontal stabilizer trim actuator is completed, the pre-tightening force can be re-applied by pressing the limiting block 313, and the limiting block 313 is allowed to move away from the limiting groove group 221, so that the second rod 22 can slide in the axial direction of the locking rod 20 and be reset. Specifically, the limiting groove group 221 includes a limiting groove 2211. After the second rod 22 and the limiting shell 31 have a sufficient relative displacement after the structural failure of the horizontal stabilizer trim actuator, the state of the limiting block 313 will change from Figure 3 to Figure 4 , and the limiting block 313 rotates around the axial direction of the installation shaft under the drive of the pre-tightening spring. In the circumferential direction of the second rod 22, the end of the limiting block 313 away from the installation shaft enters the limiting groove 2211, and the end surface of the limiting block 313 abuts against the groove wall of the limiting groove 2211. When the locking rod 20 is reset by pressing the limiting block 313, the state of the limiting block 313 will change from Figure 4 to Figure 3 , and the limiting block 313 reversely rotates around the axial direction of the installation shaft, the end of the limiting block 313 away from the installation shaft moves away from the limiting groove 2211, the second rod 22 is reset, and the limiting block 313 and the projection of the safety position 222 on the second rod 22 restore the overlapping state.

[0049] Further, in actual application, the locking rod 20 will rotate with the rolling screw 10. When the horizontal stabilizer trim actuator has a structural failure, in order to ensure that the limiting block 313 can timely embed in the limiting groove group 221 to limit the movement of the locking rod 20. In some embodiments of the locking structure, each limiting groove group 221 includes a plurality of limiting grooves 2211, and the plurality of limiting grooves 2211 are arranged at intervals in the circumferential direction 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 has a structural failure, the side of the limiting block 313 towards the second rod 22 has a matching limiting groove 2211, so that the limiting block 313 can smoothly embed in the limiting groove 2211, thereby effectively limiting the movement of the locking rod 20.

[0050] Further, in some embodiments of the locking structure, a plurality of sets of limiting notches 311 are spaced apart on the outer circumferential wall of the limiting shell 31 along the circumferential direction of the limiting shell 31. Each set 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 positions are provided along the circumferential direction of the second rod 22 to effectively limit the rotation of the second rod. Preferably, referring to Figure 3 and Figure 4 , the limiting notches 311 are spaced apart on the outer circumferential wall of the limiting shell 31 along the circumferential direction of the limiting shell 31 in two sets, and the two sets of limiting notches 311 are arranged opposite to each other along the radial direction of the limiting shell 31. Each set of limiting notches 311 includes two limiting notches 311, and each limiting notch 311 has a limiting block 313. In this way, after the horizontal stabilizer trim actuator completes the relevant maintenance, the limiting blocks 313 can be easily pressed to move away from the limiting grooves 2211, so that the second rod 22 is reset. Similarly, in some embodiments, if the number of limiting notches 311 along the circumferential direction of the limiting shell 31 is an even number greater than two, the two limiting notches 311 can be arranged opposite to each other.

[0051] In some embodiments of the locking structure, the limiting shell 31 is provided with a limiting hole 312 on the side facing the first rod 21, and the second rod 22 passes through the limiting hole 312. The second rod 22 has a first section 223 with an outer diameter greater 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 structurally and the second rod 22 is subjected to a pulling force in the axial direction and moves away from the limiting shell 31, it is ensured that the second rod 22 will not come out of the limiting shell 31. Preferably, in some embodiments, the limiting groove set 221 disclosed above is provided on the outer circumferential wall of the first section 223. It should be noted that when the horizontal stabilizer trim actuator is working normally, there is a gap between the end face of the end of the first section 223 facing the first rod 21 and the inner wall of the side 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 connected to the side of the limiting shell 31 away from the first rod 21 and enclosing the limiting space. In this way, when the horizontal stabilizer trim actuator fails structurally and the second rod 22 is subjected to a pressure in the axial direction and moves towards the limiting shell 31, it is ensured that the second rod 22 will not come out of the side of the limiting shell 31 away from the first rod 21. It should be noted that when the horizontal stabilizer trim actuator is working normally, there is a gap between the end face 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] Further, in some embodiments, the base 32 is provided with an ear 321 on the side away from the limiting shell 31, which can facilitate the connection of the locking structure and the fuselage structure.

[0054] The embodiments of the present application also provide 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 of the above-mentioned locking structures (it should be noted that the locking structure is blocked by the rolling screw 10 and the first connecting structure 11 in Figure 6 , and is not shown). The first connecting structure 11 is used to connect with the fuselage structure, and the second connecting structure 12 is used to connect with the wing surface (i.e. the horizontal stabilizer). The shank of the rolling screw 10 penetrates through the second connecting structure 12, and one end is connected with the first connecting structure 11. The rolling screw 10 is a hollow structure, the locking rod 20 is arranged in the rolling screw 10, and the joint 30 of the locking structure is connected with 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 the horizontal stabilizer trim actuator is abnormal, the limiting 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 the present application, the terms "first", "second" are only for the purpose of description, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined with "first", "second" can explicitly or implicitly include one or more features. In the description of the present application, the meaning of "multiple" is two or more, unless otherwise specifically limited.

[0056] In the above embodiments, the description of each embodiment has its own emphasis, and the parts not described in detail in a certain embodiment can be referred to the related description of other embodiments.

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

[0058] The above is only the preferred embodiments of the present application, and does not limit the present application in any form, but any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present application, without departing from the technical solution of the present application, still belongs to the scope of the technical solution of the present application.

Claims

1. A locking structure, characterized in that: The invention is applied to a horizontal stabilizer trim actuator, wherein 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 fixedly connected to the rolling screw (10), and the second rod (22) being used to pass through the rolling screw (10); A joint (30) is used to connect with 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 spaced apart on the second rod (22), and a safety position (222) is formed at the intervals between adjacent limiting groove groups (221). A limiting notch (311) is formed 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 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 limiting groove groups (221) at intervals, and a safety position (222) is formed at the interval between the two groups of limiting groove groups (221). 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).

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 in 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 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 pre-tightening spring is provided on the mounting shaft; When the second rod (22) moves in the axial direction of the locking rod (20) in a direction away from the limiting housing (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 spaced apart 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 circumference 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) includes two, and each limiting notch (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), the base (32) being connected to a side of the limiting shell (31) facing away from the first rod (21) and enclosing the limiting space.

9. The locking structure according to claim 8, characterized in that: A lug (321) is protruding from one 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 a side facing the first rod (21); the second rod (22) is inserted into the limiting hole (312); and the second rod (22) has a first section (223) whose outer diameter is larger than the inner diameter of the limiting hole (312); the first section (223) is located in the limiting space.

11. A horizontal stabilizer trim actuator, characterized in that: The invention comprises a first connecting structure (11), a second connecting structure (12), a rolling screw (10) and any one of the locking structures disclosed in claims 1 to 10, wherein the first connecting structure (11) is used to connect to the fuselage structure, the second connecting structure (12) is used to connect to the wing surface, 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, the locking rod (20) is passed through the rolling screw (10), and 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 operates 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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