Large sweepback flap driving mechanism

Abstract

The invention provides a large sweepback flap driving mechanism which comprises a steering engine assembly, a driving rotating shaft, a rotating shaft support, a rocker arm, a fixed connecting rod, a supporting connecting rod and a connecting rod support, one end of the steering engine assembly is fixedly connected with a fuselage, and the other end of the steering engine assembly is rotationally connected with the driving rotating shaft; the driving rotating shaft is rotationally connected with the rotating shaft support; the rotating shaft support is fixedly connected with the machine body to support the driving rotating shaft; the rocker arm is rotationally connected with the driving rotating shaft and the fixed connecting rod; the fixed connecting rod is fixedly connected with the flap assembly; two ends of the supporting connecting rod are rotationally connected with the fixed connecting rod and the connecting rod support; the connecting rod support is fixedly connected with the machine body to support the supporting connecting rod; according to the large-sweepback flap driving mechanism, the driving rotating shaft is driven to rotate through stretching and retracting of the steering engine assembly, and the flap assembly is retracted and released parallel to the course through the driving rotating shaft, the rocker arm, the fixed connecting rod and the supporting connecting rod four-connecting-rod mechanism. According to the flap driving mechanism, the risk that the sliding rail is jammed due to uneven stress in the retracting and releasing process is avoided, and meanwhile the occupied space is smaller.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft flaps, in particular to a large swept-angle flap driving mechanism. Background Art

[0002] In order to increase the maximum lift coefficient, improve the aerodynamic performance of the aircraft, reduce the stall speed at high angles of attack, and reduce the take-off and landing distances, various forms of trailing edge flaps are used in aircraft design. Among them, single-slotted flaps are the most widely used in small aircraft and drones as a simple trailing edge flap. Usually, single-slotted flaps achieve backward translation and downward rotation through an articulated connecting rod or a slide rail mechanism. However, the current flap design can usually only be retracted and extended in a direction perpendicular to the trailing edge of the wing, such as Fig.10 As shown in (a) and 10(b), this flap design has little effect on the aerodynamic lift-enhancing effect when used on straight wings or wings with a small sweep angle. However, if used on high-speed wings with a large sweep angle, the aerodynamic loss is large and the lift-enhancing effect is not obvious. Generally, the aerodynamic loss caused by the large sweep angle can only be compensated by increasing the length or area of ​​the flap. Summary of the invention

[0003] The present invention aims to solve at least one of the technical problems existing in the prior art.

[0004] The invention provides a large swept-angle flap driving mechanism, which comprises: a steering gear assembly, a driving shaft, a shaft support, a rocker arm, a fixed connecting rod, a supporting connecting rod and a connecting rod support, wherein one end of the steering gear assembly is fixedly connected to a fuselage, and the other end is rotatably connected to the driving shaft; the driving shaft is rotatably connected to the shaft support; the shaft support is fixedly connected to the fuselage to support the driving shaft; the rocker arm is rotatably connected to the driving shaft and the fixed connecting rod respectively; the fixed connecting rod is fixedly connected to the flap assembly; the two ends of the supporting connecting rod are rotatably connected to the fixed connecting rod and the connecting rod support respectively; the connecting rod support is fixedly connected to the fuselage to support the supporting connecting rod; wherein the large swept-angle flap driving mechanism drives the driving shaft to rotate through the extension and retraction of the steering gear assembly, and realizes the retraction and extension of the flap assembly parallel to the heading through a four-bar linkage mechanism of the driving shaft, the rocker arm, the fixed connecting rod and the supporting connecting rod.

[0005] Furthermore, the steering gear assembly includes a steering gear support and a linear steering gear, the steering gear support is fixedly connected to the fuselage, and the linear steering gear is rotationally connected to the steering gear support and the driving shaft respectively.

[0006] Furthermore, the linear steering gear is connected to the steering gear support and the driving shaft respectively by hinges.

[0007] Furthermore, the large swept-angle flap drive mechanism also includes a first hinge connecting shaft and a first ball joint connecting shaft. The rocker arm is hingedly connected to the driving shaft through the first hinge connecting shaft, and the first hinge connecting shaft is perpendicular to the axis of the driving shaft; the rocker arm is ball-jointedly connected to the fixed connecting rod through the first ball joint connecting shaft.

[0008] Furthermore, the large swept-angle flap drive mechanism also includes a second hinge connecting shaft and a second ball joint connecting shaft, the fixed connecting rod is hingedly connected to the supporting connecting rod through the second hinge connecting shaft, and the supporting connecting rod is ball-jointedly connected to the connecting rod support through the second ball joint connecting shaft.

[0009] Furthermore, during takeoff or landing of the aircraft, the flap assembly realizes a translational movement backward and downward along the heading, as well as a downward rotation, under the action of the four-link driving shaft, rocker arm, fixed link and supporting link.

[0010] Furthermore, when the flap assembly is in the lowered state, the fixed link and the rocker arm are in a colinear state and are subject to tension.

[0011] Furthermore, there are two rotating shaft supports, and the two rotating shaft supports are rotatably connected to two ends of the driving rotating shaft respectively.

[0012] Furthermore, the number of the rocker arms, fixed links, supporting links and link supports are two each, and the two rotating shaft supports, the two rocker arms, the two fixed links, the two supporting links and the two link supports are arranged in a one-to-one correspondence.

[0013] Furthermore, the driving shaft comprises a shaft body and an ear piece, one end of the ear piece is rotationally connected to the linear servo, and the other end is fixedly connected to the shaft body.

[0014] By applying the technical solution of the present invention, a large swept-angle flap driving mechanism is provided, which drives the driving shaft to rotate through the extension and retraction of the servo assembly, and realizes the retraction and extension of the flap assembly parallel to the heading through the driving shaft, rocker arm, fixed connecting rod and supporting connecting rod four-bar linkage. Compared with the existing flap retraction and extension mechanism of the slide rail structure, the flap driving mechanism of the present invention can be fixed at the trailing edge position of the large swept-angle wing, has a simple structure and high reliability, avoids the risk of the slide rail being stuck due to uneven force during the retraction and extension process, and occupies less space. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The included drawings are used to provide a further understanding of the embodiments of the present invention, which constitute a part of the specification, are used to illustrate the embodiments of the present invention, and together with the text description, explain the principles of the present invention. Obviously, the drawings in the following description are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0016] Figure 1 A schematic structural diagram of a large swept-angle flap driving mechanism provided according to a specific embodiment of the present invention is shown;

[0017] Figure 2 Shows Figure 1 A magnified schematic diagram of the local A in the middle;

[0018] Figure 3 Shows Figure 1 A magnified schematic diagram of the part B in the middle;

[0019] Figure 4 A schematic diagram of the retraction and extension of a flap assembly parallel to the heading provided in a specific embodiment of the present invention is shown;

[0020] Figure 5 A schematic diagram of the flap assembly in the retracted state in a top view of the aircraft is shown;

[0021] Figure 6 A schematic diagram of the flap assembly in a down position in a top view of the aircraft is shown;

[0022] Figure 7 It shows a schematic structural diagram of a hinge connecting shaft provided according to a specific embodiment of the present invention;

[0023] Figure 8 It shows a schematic structural diagram of a ball joint connecting shaft provided according to a specific embodiment of the present invention;

[0024] Fig. 9 (a) and 9(b) respectively show the retracted state and the lowered state of the flap parallel to the heading motion in the present invention;

[0025] Fig.10 (a) and 10 (b) respectively show the retracted state and the lowered state of the flap in the prior art, in which the flap moves perpendicular to the trailing edge.

[0026] The above drawings include the following reference numerals:

[0027] 1. Servo support; 2. Linear servo; 3. Drive shaft; 31. Ear; 32. Shaft body; 4. Shaft support; 5. Rocker arm; 6. Fixed connecting rod; 7. Support connecting rod; 8. Connecting rod support; 9. First hinge connecting shaft; 10. First ball joint connecting shaft; 11. Second hinge connecting shaft; 12. Second ball joint connecting shaft; 200. Flap assembly. DETAILED DESCRIPTION

[0028] It should be noted that, in the absence of conflict, the embodiments in this application and the features in the embodiments can be combined with each other. The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. The following description of at least one exemplary embodiment is actually only illustrative and is by no means intended to limit the present invention and its application or use. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0029] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0030] Unless otherwise specifically stated, the relative arrangement, numerical expressions and numerical values ​​of the parts and steps set forth in these embodiments do not limit the scope of the present invention. Meanwhile, it should be understood that, for ease of description, the sizes of the various parts shown in the accompanying drawings are not drawn according to the actual proportional relationship. The technology, method and equipment known to those of ordinary skill in the relevant art may not be discussed in detail, but in appropriate cases, the technology, method and equipment should be considered as a part of the specification. In all examples shown and discussed here, any specific value should be interpreted as being merely exemplary, rather than as a limitation. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters represent similar items in the following drawings, and therefore, once a certain item is defined in an accompanying drawing, it does not need to be further discussed in subsequent drawings.

[0031] like Figure 1As shown, according to a specific embodiment of the present invention, a large swept-angle flap drive mechanism is provided, which includes: a steering gear assembly, a driving shaft 3, a shaft support 4, a rocker arm 5, a fixed link 6, a supporting link 7 and a link support 8, wherein one end of the steering gear assembly is fixedly connected to the fuselage, and the other end is rotatably connected to the driving shaft 3; the driving shaft 3 is rotatably connected to the shaft support 4; the shaft support 4 is fixedly connected to the fuselage to support the driving shaft 3; the rocker arm 5 is rotatably connected to the driving shaft 3 and the fixed link 6 respectively; the fixed link 6 is fixedly connected to the flap assembly 200; the two ends of the supporting link 7 are rotatably connected to the fixed link 6 and the link support 8 respectively; the link support 8 is fixedly connected to the fuselage to support the supporting link 7; wherein, the large swept-angle flap drive mechanism drives the driving shaft 3 to rotate through the extension and retraction of the steering gear assembly, and realizes the retraction and extension of the flap assembly 200 parallel to the heading through the four-bar linkage mechanism of the driving shaft 3, the rocker arm 5, the fixed link 6 and the supporting link 7.

[0032] By applying this configuration, a large swept-angle flap driving mechanism is provided, which drives the driving shaft 3 to rotate through the extension and retraction of the servo assembly, and realizes the retraction and extension of the flap assembly 200 parallel to the heading through the four-bar linkage mechanism of the driving shaft 3, the rocker arm 5, the fixed connecting rod 6 and the supporting connecting rod 7. Compared with the existing flap retracting and extending mechanism with a slide rail structure, the flap driving mechanism of the present invention can be fixed at the trailing edge position of the large swept-angle wing, has a simple structure, high reliability, avoids the risk of the slide rail being stuck due to uneven force during the retraction and extension process, and occupies less space.

[0033] Further, in the present invention, if Figure 1 As shown, in order to realize the driving of the driving shaft 3 by the servo assembly, the servo assembly can be configured to include a servo support 1 and a linear servo 2, the servo support 1 is fixedly connected to the fuselage, and the linear servo 2 is rotatably connected to the servo support 1 and the driving shaft 3 respectively.

[0034] By applying this configuration, the flap retraction and extension process can be limited only by the stroke of the linear servo 2. During the flight of the aircraft, the flap assembly 200 is in the retracted state, the flap assembly 200 fits the wing perfectly, and the aerodynamic load is transmitted to the linear servo 2 through the four-bar linkage of the drive shaft 3, the rocker arm 5, the fixed connecting rod 6 and the supporting connecting rod 7. The linear servo 2 has a screw connecting rod mechanism inside, which has a self-locking function and is used to bear the aerodynamic load when the flap is in the retracted state. During the take-off or landing process of the aircraft, the linear servo 2 extends under the electric or hydraulic drive, driving the drive shaft 3 to rotate, so as to realize the retraction and extension of the flap assembly 200 parallel to the heading.

[0035] As a specific embodiment of the present invention, the linear servo 2 can be hingedly connected to the servo support 1 and the driving shaft 3. For example, a hinge connection shaft can be used to realize the hinge connection.

[0036] Further, in the present invention, if Figure 2 As shown, in order to realize the linkage between the driving shaft 3, the rocker arm 5 and the fixed connecting rod 6, the large swept-angle flap driving mechanism can be configured to also include a first hinge connecting shaft 9 and a first ball joint connecting shaft 10. The rocker arm 5 is hingedly connected to the driving shaft 3 through the first hinge connecting shaft 9, and the first hinge connecting shaft 9 is perpendicular to the axis of the driving shaft 3; the rocker arm 5 is ball-jointedly connected to the fixed connecting rod 6 through the first ball joint connecting shaft 10.

[0037] With this configuration, during the take-off or landing of the aircraft, due to the four-bar connection, under the rotation of the driving shaft 3, the rocker arm 5 moves in space, rotating around the axis of the driving shaft 3 on the one hand, and rotating around the hinge connection axis on the other hand. Figure 2 As shown by the middle arrow, under the rotation of the rocker arm 5, the fixed link 6 moves backward along the heading.

[0038] Further, in the present invention, if Figure 3 As shown, in order to realize the linkage between the fixed link 6 and the supporting link 7, the large swept-angle flap drive mechanism can be configured to also include a second hinge connecting shaft 11 and a second ball joint connecting shaft 12. The fixed link 6 is hingedly connected to the supporting link 7 through the second hinge connecting shaft 11, and the supporting link 7 is ball-jointedly connected to the link support 8 through the second ball joint connecting shaft 12.

[0039] With this configuration, the support link 7 moves in space around the second ball joint connection axis 12 under the rotation of the fixed link 6. The fixed link 6 moves backward along the heading under the rotation of the rocker arm 5, and at the same time, due to the rotation of the support link 7, the fixed link 6 moves backward and downward along the heading. The fixed link 6 is fixedly connected to the flap assembly 200. Under the constraints of the support link 7 and the rocker arm 5, the flap assembly 200 moves backward and downward along the heading, and rotates downward, as shown in FIG. Figures 4 to 6 shown.

[0040] When the flap assembly 200 reaches the specified position under the drive of the linear servo 2 and the flap is in the lowered state, the aerodynamic force it receives is significantly greater than that in the retracted state. At this time, the fixed link 6 and the rocker arm 5 are just in line and are subject to tension. The fixed link 6, the rocker arm 5, the supporting link 7 and the support form a triangular stable structure, which can bear the aerodynamic load alone, and the linear servo 2 is no longer subjected to force.

[0041] Furthermore, in the present invention, in order to improve the stability of the drive shaft 3 during the flap movement, the number of the configurable shaft supports 4 can be set to be multiple, for example, two or three, etc., to improve the stable support of the drive shaft 3. Figure 1 As shown, two rotating shaft supports 4 may be provided, and the two rotating shaft supports 4 are rotatably connected to the two ends of the driving rotating shaft 3 respectively.

[0042] As a specific embodiment of the present invention, the driving shaft 3 and the shaft support 4 can also be connected by a hinge to achieve the rotation of the driving shaft 3 along the shaft axis.

[0043] Furthermore, in the present invention, in order to further improve the stability of the flap during movement, the number of the rocker arm 5, the fixed link 6, the support link 7 and the link support 8 can be configured to be multiple, and the rocker arm 5, the fixed link 6, the support link 7 and the link support 8 are arranged one by one.

[0044] As a specific embodiment of the present invention, Figure 1 As shown, the number of the rocker arm 5, the fixed connecting rod 6, the supporting connecting rod 7 and the connecting rod support 8 can be two. The driving shaft, the two rocker arms 5, the two fixed connecting rods 6 and the two supporting connecting rods 7 form two groups of four-bar linkages.

[0045] Further, in the present invention, in order to facilitate the linear servo 2 to control the rotation of the driving shaft 3, the driving shaft 3 may be configured to include a shaft body 32 and an ear piece 31, one end of the ear piece 31 is rotatably connected to the linear servo 2, and the other end is fixedly connected to the shaft body 32. As a specific embodiment of the present invention, the ear piece 31 and the linear servo 2 may be connected by a hinge.

[0046] In the present invention, the hinge connection axis only allows the two connected parts to rotate relative to each other in the same plane, that is, there is one degree of freedom; while the ball joint connection axis allows the two connected parts to rotate relative to each other in space, that is, there are three degrees of freedom.

[0047] The large swept-back flap drive mechanism of the present invention realizes the backward and downward translation parallel to the heading direction and realizes the small-angle downward rotation through two sets of simple four-bar linkages. Fig. 9 (a) and Fig. 9 Compared with the existing flap retracting and extending mechanism with a slide rail structure, the four-link structure of the present invention is simple, highly reliable, avoids the risk of slide rail jamming due to uneven force during the retracting and extending process, and occupies less space.

[0048] In order to have a further understanding of the present invention, the large swept-angle flap driving mechanism of the present invention is described in detail below with reference to the accompanying drawings.

[0049] like Figures 1 to 8As shown, according to a specific embodiment of the present invention, a large swept angle flap drive mechanism is provided, comprising a steering gear assembly, a driving shaft 3, two shaft supports 4, two rocker arms 5, two fixed connecting rods 6, two supporting connecting rods 7, two connecting rod supports 8, a first hinge connecting shaft 9, a first ball joint connecting shaft 10, a second hinge connecting shaft 11 and a second ball joint connecting shaft 12. The two shaft supports 4, the two rocker arms 5, the two fixed connecting rods 6, the two supporting connecting rods 7, the two connecting rod supports 8 are arranged in a one-to-one correspondence, and form two groups of four-bar mechanisms with the driving shaft 3.

[0050] The servo assembly comprises a servo support 1 and a linear servo 2. The servo support 1 is fixedly connected to the fuselage, and the linear servo 2 is rotatably connected to the servo support 1 and the ear piece 31 of the driving shaft 3 respectively.

[0051] During the flight of the aircraft, the linear actuator 2 is in a shortened and self-locking state, the flap assembly 200 is in a retracted state, the flap assembly 200 is in a good fit with the wing, and the aerodynamic load is transmitted to the linear actuator 2 through the four-bar linkage of the drive shaft 3, the rocker arm 5, the fixed link 6 and the support link 7. During the take-off or landing process of the aircraft, the linear actuator 2 is extended by electric or hydraulic drive, such as Figure 2 As shown, the driving shaft 3 is driven to rotate clockwise.

[0052] The rocker arm 5 is hinged to the driving shaft 3 via a first hinge connection shaft 9, and the first hinge connection shaft 9 is perpendicular to the axis of the driving shaft 3; the rocker arm 5 is spherically connected to the fixed connecting rod 6 via a first spherical joint connection shaft 10. The fixed connecting rod 6 is hinged to the supporting connecting rod 7 via a second hinge connection shaft 11, and the supporting connecting rod 7 is spherically connected to the connecting rod support 8 via a second spherical joint connection shaft 12.

[0053] The steering gear support 1, the shaft support 4 and the connecting rod support 8 are fixed on the body structure and remain stationary during the entire movement of the flap.

[0054] During takeoff or landing of the aircraft, the rocker arm 5 rotates around the first hinge shaft 9, and the driving shaft 3 drives the rocker arm 5 to rotate clockwise, thereby pushing the fixed link 6 to move backward along the heading. Under the restraint of the supporting link 7 and the rocker arm 5, the flap assembly 200 moves backward and downward along the heading and rotates downward.

[0055] When the flap assembly 200 reaches the specified position under the drive of the linear servo 2 and the flap is in the lowered state, the fixed link 6 and the rocker arm 5 are just in line and are subject to tension. The fixed link 6, the rocker arm 5, the supporting link 7 and the support form a triangular stable structure, and the linear servo 2 is not subjected to force.

[0056] In addition, it should be noted that the use of terms such as "first" and "second" to limit components is only for the convenience of distinguishing the corresponding components. If not otherwise stated, the above terms have no special meaning and therefore cannot be understood as limiting the scope of protection of the present invention.

[0057] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A large swept angle flap drive mechanism, characterized in that: The high-sweep-angle flap driving mechanism comprises: a steering gear assembly, a driving shaft (3), a shaft support (4), a rocker arm (5), a fixed connecting rod (6), a supporting connecting rod (7) and a connecting rod support (8); one end of the steering gear assembly is fixedly connected to the fuselage, and the other end is rotatably connected to the driving shaft (3); the driving shaft (3) is rotatably connected to the shaft support (4); the shaft support (4) is fixedly connected to the fuselage to support the driving shaft (3); the rocker arm (5) is rotatably connected to the driving shaft (3) and the fixed connecting rod (6) respectively; the fixed connecting rod (6) is fixedly connected to the flap assembly (200); two ends of the supporting connecting rod (7) are rotatably connected to the fixed connecting rod (6) and the connecting rod support (8) respectively; the connecting rod support (8) is fixedly connected to the fuselage to support the supporting connecting rod (7); The large swept-angle flap driving mechanism drives the driving shaft (3) to rotate through the extension and retraction of the servo assembly, and realizes the retraction and extension of the flap assembly (200) parallel to the heading through a four-bar linkage consisting of the driving shaft (3), the rocker arm (5), the fixed connecting rod (6) and the supporting connecting rod (7).

2. The high-sweep-angle flap drive mechanism according to claim 1, characterized in that: The steering gear assembly comprises a steering gear support (1) and a linear steering gear (2); the steering gear support (1) is fixedly connected to the fuselage, and the linear steering gear (2) is rotationally connected to the steering gear support (1) and the driving shaft (3) respectively.

3. The large swept angle flap drive mechanism according to claim 2, characterized in that: The linear steering gear (2) is respectively connected to the steering gear support (1) and the driving shaft (3) by means of hinges.

4. The high-sweep-angle flap drive mechanism according to claim 1, characterized in that: The high-sweep-angle flap drive mechanism also includes a first hinge connecting shaft (9) and a first ball-joint connecting shaft (10); the rocker arm (5) is hinge-connected to the driving shaft (3) via the first hinge connecting shaft (9); the first hinge connecting shaft (9) is perpendicular to the axis of the driving shaft (3); and the rocker arm (5) is ball-jointed to the fixed connecting rod (6) via the first ball-joint connecting shaft (10).

5. The high-sweep-angle flap drive mechanism according to claim 1, characterized in that: The high-sweep-angle flap drive mechanism also includes a second hinge connecting shaft (11) and a second ball-joint connecting shaft (12); the fixed connecting rod (6) is hinge-connected to the supporting connecting rod (7) via the second hinge connecting shaft (11); and the supporting connecting rod (7) is ball-jointed to the connecting rod support (8) via the second ball-joint connecting shaft (12).

6. The high-sweep-angle flap drive mechanism according to any one of claims 1 to 5, characterized in that: During take-off or landing of the aircraft, the flap assembly realizes a translational motion backward and downward along the heading, as well as a downward rotation, under the action of the four-linkage comprising the driving shaft (3), the rocker arm (5), the fixed link (6) and the supporting link (7).

7. The high-sweep-angle flap drive mechanism according to claim 1, characterized in that: When the flap assembly is in a lowered state, the fixed connecting rod (6) and the rocker arm (5) are in a colinear state and are subject to tension.

8. The high-sweep-angle flap drive mechanism according to any one of claims 1 to 7, characterized in that: The number of the rotating shaft supports (4) is two, and the two rotating shaft supports (4) are respectively rotatably connected to the two ends of the driving rotating shaft (3).

9. The high-sweep-angle flap drive mechanism according to claim 8, characterized in that: The number of the rocker arm (5), the fixed connecting rod (6), the supporting connecting rod (7) and the connecting rod support (8) is two each, and the two rotating shaft supports (4), the two rocker arms (5), the two fixed connecting rods (6), the two supporting connecting rods (7) and the two connecting rod supports (8) are arranged in a one-to-one correspondence.

10. The high-sweep-angle flap drive mechanism according to claim 2, characterized in that: The driving shaft (3) comprises a shaft body (32) and an ear piece (31); one end of the ear piece (31) is rotatably connected to the linear servo (2), and the other end is fixedly connected to the shaft body (32).

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