An aircraft tail support

Abstract

The utility model belongs to the field of aircraft tail wing unlifting, concretely relates to an aircraft tail wing bracket. Include: support assembly, positioning assembly, lifting assembly, lifting assembly, the positioning assembly includes first positioning unit and second positioning unit, first positioning unit and second positioning unit are detachable fixed connection with support assembly respectively, through setting first positioning unit and second positioning unit, when lifting assembly and aircraft tail wing abut, first positioning unit and second positioning unit can position lifting assembly, thereby make lifting assembly can keep good contact with aircraft tail wing, improve the support effect of this aircraft tail wing bracket.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft tail fin lift-off, specifically, it relates to an aircraft tail fin support. Background Technology

[0002] With the development of society and economy, more and more people are traveling by air. When an aircraft is parked on the ground for a long time (especially during maintenance or storage), it is usually necessary to support the tail of the aircraft to prevent it from drooping due to its own weight, gravity, or strong winds.

[0003] Chinese utility model patent CN202223094029.X discloses a hinge bracket for an aircraft tail fin, including a crossbeam and a base frame. A lifting device is installed above the crossbeam, and an adjustment device is installed above the lifting device. This device can be moved to the aircraft tail fin via wheels, the base frame, and the crossbeam. Then, turning the first handle drives the first crossbar to rotate, which in turn drives the first bevel gear to rotate. The first bevel gear drives the second bevel gear to rotate, which in turn drives the first sleeve to move via the first screw. The first sleeve then moves the bracket via the first cross plate, thus adjusting the height of the connecting structure above the bracket.

[0004] The problem with this utility model is that when the bracket supports the aircraft tail, it will be subjected to the reaction force of the aircraft tail. Since the bracket is not equipped with a locking mechanism to ensure that the bracket and the aircraft tail always maintain a good contact state, under the reaction force of the aircraft tail, the first screw and the first sleeve are very likely to move relative to each other, which will make the bracket not firmly contact the aircraft tail and result in poor support effect. Utility Model Content

[0005] To solve the above problems, this utility model provides an aircraft tail fin bracket, comprising:

[0006] Support components;

[0007] The positioning component includes a first positioning unit and a second positioning unit; the first positioning unit and the second positioning unit are respectively detachably and fixedly connected to the support component.

[0008] A lifting assembly; the lifting assembly is connected to the support assembly; the first positioning unit and the second positioning unit are respectively connected to the lifting assembly;

[0009] A lifting assembly is provided, which is connected to the lifting assembly; the lifting assembly and the support assembly are spaced apart along the height direction; the first positioning unit and the second positioning unit are spaced apart from the lifting assembly along the height direction.

[0010] In some embodiments, the lifting assembly includes a lifting turntable, a drive rod, a driving gear, a driven gear, a lead screw, a solenoid, a first lifting rod, and a second lifting rod; one end of the drive rod along its axial direction is connected to the lifting turntable, and the other end is connected to the driving gear; the outer peripheral surface of the drive rod is rotatably connected to the support assembly; one end of the lead screw along its axial direction is rotatably connected to the support assembly in the vertical direction, and the other end is spaced apart from the lifting assembly; one end of the solenoid along its axial direction is connected to the lifting assembly in the vertical direction, and the other end is spaced apart from the support assembly; the outer peripheral surface of the lead screw is rotatably connected to the support assembly. The inner circumferential surface of the solenoid is threaded; the outer circumferential surface of the lead screw is fixedly connected to the inner circumferential surface of the driven gear; the driven gear is spaced apart from the solenoid; the driven gear meshes with the driving gear; one end of the first lifting rod along its axial direction is vertically connected to the lifting assembly, and the other end is spaced apart from the support assembly; one end of the second lifting rod along its axial direction is vertically connected to the lifting assembly, and the other end is spaced apart from the support assembly; the outer circumferential surface of the first lifting rod is connected to the first positioning unit; the outer circumferential surface of the second lifting rod is connected to the second positioning unit.

[0011] In some embodiments, the first positioning unit includes a first positioning turntable and a first positioning module; the interior of the first positioning module has a tubular cavity structure; one end of the first positioning module along its axial direction is vertically connected to the support component, and the other end is spaced apart from the lifting component; the inner circumferential surface of the first positioning turntable is threadedly connected to the outer circumferential surface of the first positioning module; the inner circumferential surface of the first positioning module is connected to the first lifting rod; the outer diameter of the first positioning module gradually decreases from the end away from the support component to the end close to the support component.

[0012] The second positioning unit includes a second positioning turntable and a second positioning module; the interior of the second positioning module has a tubular cavity structure; one end of the second positioning module along its axial direction is connected to the support component in the vertical direction, and the other end is spaced apart from the lifting component; the inner circumferential surface of the second positioning turntable is threadedly connected to the outer circumferential surface of the second positioning module; the inner circumferential surface of the second positioning module is connected to the second lifting rod; the outer diameter of the second positioning module gradually decreases from the end away from the support component to the end close to the support component.

[0013] In some embodiments, the first positioning module includes a first connecting portion and a plurality of first clamping portions; one end of the first clamping portion along its axial direction is fixedly connected to one end of the first connecting portion, and the other end is spaced apart from the lifting component; two adjacent first clamping portions are evenly spaced along the circumference of the first connecting portion; the plurality of first clamping portions together form a first clamping area; the first lifting rod passes through the first clamping area and abuts against the first clamping portion; the diameter of the first clamping portion gradually decreases from the end away from the first connecting portion to the end close to the first connecting portion; the end of the first connecting portion away from the first clamping portion is connected to the support component.

[0014] The second positioning module includes a second connecting part and a plurality of second clamping parts; one end of the second clamping part along its axial direction is fixedly connected to one end of the second connecting part, and the other end is spaced apart from the lifting component; two adjacent second clamping parts are evenly spaced along the circumference of the second connecting part; the plurality of second clamping parts together form a second clamping area; the second lifting rod passes through the second clamping area and abuts against the second clamping part; the diameter of the second clamping part gradually decreases from the end away from the second connecting part to the end close to the second connecting part; the end of the second connecting part away from the second clamping part is connected to the support component.

[0015] In some embodiments, the lifting assembly includes a third connecting portion, multiple support plates, and a lifting plate; one end of each support plate is connected to the lifting plate along the height direction, and the other end is connected to the third connecting portion; adjacent support plates are spaced apart; the end of the third connecting portion away from the support plate is connected to the solenoid, the first lifting rod, and the second lifting rod.

[0016] In some embodiments, the distance from the end face of the support plate near the second connecting portion to the middle of the second connecting portion gradually decreases from both ends.

[0017] In some embodiments, the thickness of the support plate gradually increases from both ends of the support plate to the middle of the support plate.

[0018] In some embodiments, the lifting assembly further includes multiple soft pads; the soft pads are fixedly connected to one end of the lifting plate away from the second connecting portion.

[0019] In some embodiments, the thickness of the soft pad gradually decreases from both ends of the support plate to near the middle of the support plate.

[0020] In some embodiments, the support assembly includes a support frame, a plurality of casters, and a plurality of adjustable feet; the support frame includes a support base plate, a first support tube, a second support tube, and a support seat; one end of the support base plate in the vertical direction is connected to the fixed end of the caster, and the other end is connected to one end of the first support tube along its axis and one end of the second support tube along its axis; the adjustable feet are threadedly connected to the support base plate; the support seat is fixedly connected to the end of the support base plate away from the caster; the first connecting portion is connected to the end of the first support tube away from the caster; the second connecting portion is connected to the end of the second support tube away from the caster; the support seat is rotatably connected to the drive rod; and the support seat is rotatably connected to the end of the lead screw away from the third connecting portion.

[0021] To solve the above problems, this utility model has the following advantages:

[0022] By setting up a first positioning unit and a second positioning unit, when the lifting component comes into contact with the aircraft tail, the first positioning unit and the second positioning unit can position the lifting component, thereby ensuring that the lifting component can maintain good contact with the aircraft tail and improving the support effect of the aircraft tail bracket. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the overall structure of an aircraft tail fin bracket in some embodiments;

[0024] Figure 2 This is a schematic diagram of the overall structure of an aircraft tail fin bracket in some embodiments;

[0025] Figure 3 This is a schematic diagram of the overall structure of an aircraft tail fin bracket in some embodiments;

[0026] Figure 4 This is a structural schematic diagram of the first positioning module;

[0027] Figure 5 for Figure 4 Cross-sectional view along the AA direction;

[0028] Figure 6 for Figure 1 A magnified view of a portion of point A in the middle.

[0029] In the diagram: 100-Support assembly; 110-Support frame; 111-Support base plate; 112-First support tube; 113-Second support tube; 114-Support base; 120-Universal wheel; 130-Adjustable feet; 200-Positioning assembly; 210-First positioning unit; 211-First positioning turntable; 212-First positioning module; 2121-First connecting part; 2122-First clamping part; 220-Second positioning unit; 221-Second positioning module 222-Second positioning module; 2221-Second connecting part; 2222-Second clamping part; 300-Lifting assembly; 310-Lifting turntable; 320-Drive rod; 330-Driving gear; 340-Driven gear; 350-Screw; 360-Screw tube; 370-First lifting rod; 380-Second lifting rod; 400-Lifting assembly; 410-Third connecting part; 420-Support plate; 430-Lifting plate; 440-Soft pad. Detailed Implementation

[0030] The present disclosure will now be discussed with reference to several exemplary embodiments. It should be understood that these embodiments are discussed only to enable those skilled in the art to better understand and thus implement the present disclosure, and are not intended to imply any limitation on the scope of the disclosure.

[0031] As used herein, the term "comprising" and its variations are to be interpreted as open-ended terms meaning "including but not limited to". The term "based on" is to be interpreted as "at least partially based on". The terms "one embodiment" and "an embodiment" are to be interpreted as "at least one embodiment". The term "another embodiment" is to be interpreted as "at least one other embodiment". The terms "upper", "lower", "left", "right", "front", "rear", "top", "bottom", "inner", "outer", "vertical", "horizontal", "lateral", "longitudinal", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings. These terms are primarily for the purpose of better describing this application and its embodiments and are not intended to limit the indicated devices, elements, or components to having a specific orientation or being constructed and operated in a specific orientation. Furthermore, some of the above terms may be used to indicate other meanings besides orientations or positional relationships; for example, the term "upper" may in some cases indicate a dependency or connection relationship. Those skilled in the art can understand the specific meaning of these terms in this application according to the specific circumstances. In addition, the terms "installed", "set up", "equipped with", "connected", and "linked" should be interpreted broadly. For example, it can be a fixed connection, a detachable connection, or an integral structure; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, or an internal connection between two devices, elements, or components. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances. Furthermore, the terms "first," "second," etc., are mainly used to distinguish different devices, elements, or components (the specific types and structures may be the same or different), and are not used to indicate or imply the relative importance or quantity of the indicated devices, elements, or components. Unless otherwise stated, "a plurality of" means two or more.

[0032] This embodiment discloses an aircraft tail fin bracket, such as Figure 1 , Figure 2 , Figure 3 As shown, it may include:

[0033] Support component 100; positioning component 200; lifting component 300; lifting component 400; the positioning component 200 includes a first positioning unit 210 and a second positioning unit 220; the first positioning unit 210 and the second positioning unit 220 are respectively detachably fixedly connected to the support component 100; the lifting component 300 is connected to the support component 100; the first positioning unit 210 and the second positioning unit 220 are respectively connected to the lifting component 300; the lifting component 400 is connected to the lifting component 300; the lifting component 400 and the support component 100 are spaced apart along the height direction; the first positioning unit 210 and the second positioning unit 220 are spaced apart from the lifting component 400 along the height direction.

[0034] In this embodiment, by setting a first positioning unit 210 and a second positioning unit 220, when the lifting component 400 comes into contact with the aircraft tail, the first positioning unit 210 and the second positioning unit 220 can position the lifting component 400, thereby enabling the lifting component 400 to maintain good contact with the aircraft tail, so as to improve the support effect of the aircraft tail bracket.

[0035] In some embodiments of this utility model, such as Figure 1 , Figure 2 , Figure 3 , Figure 6As shown, the lifting assembly 300 includes a lifting turntable 310, a drive rod 320, a driving gear 330, a driven gear 340, a lead screw 350, a solenoid 360, a first lifting rod 370, and a second lifting rod 380. One end of the drive rod 320 along its axial direction is connected to the lifting turntable 310, and the other end is connected to the driving gear 330. The outer circumferential surface of the drive rod 320 is rotatably connected to the support assembly 100. One end of the lead screw 350 along its axial direction is rotatably connected to the support assembly 100 in the vertical direction, and the other end is spaced apart from the lifting assembly 400. One end of the solenoid 360 along its axial direction is connected to the lifting assembly 400 in the vertical direction, and the other end is spaced apart from the support assembly 100. The outer circumferential surface of the lead screw 350 is rotatably connected to the support assembly 100. The outer circumferential surface of the screw 350 is threadedly connected to the inner circumferential surface of the lead screw 360; the outer circumferential surface of the lead screw 350 is fixedly connected to the inner circumferential surface of the driven gear 340; the driven gear 340 is spaced apart from the screw 360; the driven gear 340 is meshed with the driving gear 330; one end of the first lifting rod 370 along its axial direction is vertically connected to the lifting assembly 400, and the other end is spaced apart from the support assembly 100; one end of the second lifting rod 380 along its axial direction is vertically connected to the lifting assembly 400, and the other end is spaced apart from the support assembly 100; the outer circumferential surface of the first lifting rod 370 is connected to the first positioning unit 210; the outer circumferential surface of the second lifting rod 380 is connected to the second positioning unit 220.

[0036] In this embodiment, when it is necessary to lift the lifting assembly 400, the first positioning unit 210 and the second positioning unit 220 are released, allowing the first lifting rod 370 and the second lifting rod 380 to move relative to the first positioning unit 210 and the second positioning unit 220. Then, the lifting turntable 310 is raised, causing the driving gear 330 to drive the driven gear 340 to rotate, thereby causing the lead screw 350 to rotate. The lead screw 350 drives the solenoid 360 to push the lifting assembly 400 upward to abut against the aircraft tail. Subsequently, the positions of the first lifting rod 370 and the second lifting rod 380 are locked by the first positioning unit 210 and the second positioning unit 220 respectively, ensuring that the lifting assembly 400 maintains a good abutment state with the aircraft tail. In this embodiment, as... Figure 6 As shown, the driving gear 330 and the driven gear 340 mesh together to form a bevel gear that rotates, thus enabling the lead screw 350 to rotate when the driving gear 330 drives the driven gear 340 to rotate.

[0037] In some embodiments of this utility model, such as Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5As shown,

[0038] The first positioning unit 210 includes a first positioning turntable 211 and a first positioning module 212; the interior of the first positioning module 212 has a tubular cavity structure; one end of the first positioning module 212 along its axial direction is vertically connected to the support component 100, and the other end is spaced apart from the lifting component 400; the inner circumferential surface of the first positioning turntable 211 is threadedly connected to the outer circumferential surface of the first positioning module 212; the inner circumferential surface of the first positioning module 212 is connected to the first lifting rod 370; the outer diameter of the first positioning module 212 gradually decreases from the end away from the support component 100 to the end close to the support component 100.

[0039] The second positioning unit 220 includes a second positioning turntable 221 and a second positioning module 222; the interior of the second positioning module 222 has a tubular cavity structure; one end of the second positioning module 222 along its axial direction is vertically connected to the support component 100, and the other end is spaced apart from the lifting component 400; the inner circumferential surface of the second positioning turntable 221 is threadedly connected to the outer circumferential surface of the second positioning module 222; the inner circumferential surface of the second positioning module 222 is connected to the second lifting rod 380; the outer diameter of the second positioning module 222 gradually decreases from the end away from the support component 100 to the end close to the support component 100.

[0040] The first positioning module 212 includes a first connecting portion 2121 and a plurality of first clamping portions 2122; one end of the first clamping portion 2122 along its axial direction is fixedly connected to one end of the first connecting portion 2121, and the other end is spaced apart from the lifting component 400; two adjacent first clamping portions 2122 are evenly spaced along the circumference of the first connecting portion 2121; the plurality of first clamping portions 2122 together form a first clamping area; the first lifting rod 370 passes through the first clamping area and abuts against the first clamping portion 2122; the diameter of the first clamping portion 2122 gradually decreases from the end away from the first connecting portion 2121 to the end close to the first connecting portion 2121; the end of the first connecting portion 2121 away from the first clamping portion 2122 is connected to the support component 100;

[0041] The second positioning module 222 includes a second connecting part 2221 and a plurality of second clamping parts 2222; one end of the second clamping part 2222 along its axial direction is fixedly connected to one end of the second connecting part 2221, and the other end is spaced apart from the lifting component 400; two adjacent second clamping parts 2222 are evenly spaced along the circumference of the second connecting part 2221; the plurality of second clamping parts 2222 together form a second clamping area; the second lifting rod 380 passes through the second clamping area and abuts against the second clamping part 2222; the diameter of the second clamping part 2222 gradually decreases from the end away from the second connecting part 2221 to the end close to the second connecting part 2221; the end of the second connecting part 2221 away from the second clamping part 2222 is connected to the support component 100.

[0042] In this embodiment, since the multiple first locking portions 2122 are spaced apart, and the multiple second locking portions 2222 are spaced apart, and the diameter of the first locking portions 2122 gradually decreases from the end away from the first connecting portion 2121 to the end near the first connecting portion 2121, and the diameter of the second locking portions 2222 gradually decreases from the end away from the second connecting portion 2221 to the end near the second connecting portion 2221, it can be imagined that when the first positioning turntable 211 and the second positioning turntable 221 rotate, there is a state where the first locking portion 2122 presses the first lifting rod 370 along the radial direction of the first locking area, and the second locking portion 2222 presses the second lifting rod 380 along the radial direction of the second locking area, and finally the first locking portion 2122 locks the position of the first lifting rod 370, and the second locking portion 2222 locks the position of the second lifting rod 380; in this embodiment, it can be imagined that the first connecting portion 2122... Holes are provided on the first lifting rod 370 and the second lifting rod 380 respectively, and the first lifting rod 370 and the second lifting rod 380 can pass through the holes on the first connecting part 2121 and the second connecting part 2221 respectively. In this embodiment, in order to facilitate the threaded connection between the first positioning turntable 211 and the first clamping part 2122, the taper of the first clamping part 2122 can be selectively adjusted according to actual needs, while ensuring that the first clamping part 2122 can clamp the first lifting rod 370. This facilitates the first positioning turntable 211 to spirally enter the first clamping part 2122 from the end of the first clamping part 2122 away from the first connecting part 2121. Furthermore, according to actual needs, a certain taper can be provided at the part where the inner circumferential surface of the first positioning turntable 211 connects with the first clamping part 2122, so as to facilitate the first lifting positioning turntable to screw into the first clamping part 2122. Similarly, the second clamping part 2222 and the second positioning turntable 221 are also treated in this way.

[0043] In some embodiments of this utility model, such as Figure 1 , Figure 2 , Figure 3 As shown, the lifting assembly 400 includes a third connecting part 410, multiple support plates 420, and a lifting plate 430; one end of the support plate 420 along the height direction is connected to the lifting plate 430, and the other end is connected to the third connecting part 410; adjacent support plates 420 are spaced apart; the end of the third connecting part 410 away from the support plate 420 is connected to the screw tube 360, the first lifting rod 370, and the second lifting rod 380.

[0044] In this embodiment, when the solenoid 360 moves upward, it can push the third connecting part 410 to move upward, and finally make the lifting plate 430 abut against the tail of the aircraft.

[0045] In some embodiments of this utility model, such as Figure 1 , Figure 2 , Figure 3 As shown, the distance between the end face of the lifting plate 430 and the second connecting portion 2221 gradually decreases from both ends toward the middle.

[0046] In this embodiment, by setting the support plate 430 to an arc shape, it can more closely resemble the shape of the aircraft tail fin, thereby achieving a larger contact area with the aircraft tail fin and further enhancing the support effect on the aircraft tail fin.

[0047] In some embodiments of this utility model, such as Figure 1 , Figure 2 , Figure 3 As shown, the thickness of the support plate 420 gradually increases from both ends of the lifting plate 430 to the middle of the lifting plate 430.

[0048] In this embodiment, it can be imagined that the middle part of the support plate 430 plays the most important supporting role, and its force on the aircraft tail is basically in the vertical direction, while the force on the aircraft at both ends of the support plate 430 is relatively small. Therefore, by making the support plate 420 in the middle of the support plate 430 slightly thicker, it is possible to prevent the support plate 420 from breaking. Furthermore, by making the support plates 420 at both ends of the support plate 430 slightly thinner, it is possible to save materials, further reduce the weight of the bracket, and also save costs.

[0049] In some embodiments of this utility model, such as Figure 1 , Figure 2 , Figure 3 As shown, the lifting assembly 400 also includes multiple soft pads 440; the soft pads 440 are fixedly connected to one end of the lifting plate 430 away from the second connecting part 2221; the thickness of the soft pads 440 gradually decreases from both ends of the lifting plate 430 to near the middle of the lifting plate 430.

[0050] In this embodiment, the soft pad 440 can be made of rubber or some soft plastic. Its function is to buffer and prevent the support plate 430 from making hard contact with the aircraft tail, thus avoiding damage to the aircraft tail. In this embodiment, the curvature of the support plate 430 can be set according to actual needs, and the shape and thickness of the soft pad 440 can also be set according to actual needs, and are not limited to the method described in this utility model.

[0051] In some embodiments of this utility model, such as Figure 1 , Figure 2 , Figure 3 As shown, the support assembly 100 includes a support frame 110, multiple casters 120, and multiple adjustable feet 130; the support frame 110 includes a support base plate 111, a first support tube 112, a second support tube 113, and a support seat 114; one end of the support base plate 111 in the vertical direction is connected to the fixed end of the caster 120, and the other end is connected to one end of the first support tube 112 along the axial direction and one end of the second support tube 113 along the axial direction; the adjustable feet 130 are connected to the support base plate. 111 Threaded connection; the support base 114 is fixedly connected to the end of the support base plate 111 away from the universal wheel 120; the first connecting part 2121 is connected to the end of the first support tube 112 away from the universal wheel 120; the second connecting part 2221 is connected to the end of the second support tube 113 away from the universal wheel 120; the support base 114 is rotatably connected to the drive rod 320; the support base 114 is rotatably connected to the end of the lead screw 350 away from the third connecting part 410.

[0052] The working principle of this utility model is as follows:

[0053] When it is necessary to raise the lifting assembly 400, the first positioning unit 210 and the second positioning unit 220 are released, allowing the first lifting rod 370 and the second lifting rod 380 to move relative to the first positioning unit 210 and the second positioning unit 220. Then, the lifting turntable 310 raises the drive gear 330, causing the driven gear 340 to rotate, thereby causing the lead screw 350 to rotate. The lead screw 350 drives the solenoid 360 to push the lifting assembly 400 upward to abut against the aircraft tail. Then, the positions of the first lifting rod 370 and the second lifting rod 380 are locked by the first positioning unit 210 and the second positioning unit 220 respectively, so that the lifting assembly 400 can always maintain a good abutment state with the aircraft tail.

[0054] Those skilled in the art will understand that the above embodiments are specific examples of implementing this disclosure, and in practical applications, various changes can be made in form and detail without departing from the spirit and scope of this disclosure.

Claims

1. An aircraft tail fin bracket, characterized in that, include: Support components; A positioning component, the positioning component comprising a first positioning unit and a second positioning unit; The first positioning unit and the second positioning unit are respectively detachably and fixedly connected to the support assembly; Lifting components; The lifting assembly is connected to the support assembly; The first positioning unit and the second positioning unit are respectively connected to the lifting assembly; A lifting assembly is provided, which is connected to the lifting assembly; the lifting assembly and the support assembly are spaced apart along the height direction; the first positioning unit and the second positioning unit are spaced apart from the lifting assembly along the height direction.

2. The aircraft tail fin bracket according to claim 1, characterized in that, The lifting assembly includes a lifting turntable, a drive rod, a driving gear, a driven gear, a lead screw, a solenoid, a first lifting rod, and a second lifting rod. One end of the drive rod along its axial direction is connected to the lifting turntable, and the other end is connected to the driving gear. The outer circumferential surface of the drive rod is rotatably connected to the support assembly. One end of the lead screw along its axial direction is rotatably connected to the support assembly in the vertical direction, and the other end is spaced apart from the lifting assembly. One end of the solenoid along its axial direction is connected to the lifting assembly in the vertical direction, and the other end is spaced apart from the support assembly. The outer circumferential surface of the lead screw is rotatably connected to the solenoid. The inner circumferential surface is threaded; the outer circumferential surface of the lead screw is fixedly connected to the inner circumferential surface of the driven gear; the driven gear and the threaded tube are spaced apart; the driven gear is meshed with the driving gear; one end of the first lifting rod along its axial direction is connected to the lifting assembly in the vertical direction, and the other end is spaced apart from the support assembly; one end of the second lifting rod along its axial direction is connected to the lifting assembly in the vertical direction, and the other end is spaced apart from the support assembly; the outer circumferential surface of the first lifting rod is connected to the first positioning unit; the outer circumferential surface of the second lifting rod is connected to the second positioning unit.

3. The aircraft tail fin bracket according to claim 2, characterized in that, The first positioning unit includes a first positioning turntable and a first positioning module; the interior of the first positioning module has a tubular cavity structure; one end of the first positioning module along its axial direction is vertically connected to the support component, and the other end is spaced apart from the lifting component; the inner circumferential surface of the first positioning turntable is threadedly connected to the outer circumferential surface of the first positioning module; the inner circumferential surface of the first positioning module is connected to the first lifting rod; the outer diameter of the first positioning module gradually decreases from the end away from the support component to the end close to the support component. The second positioning unit includes a second positioning turntable and a second positioning module; the interior of the second positioning module has a tubular cavity structure; one end of the second positioning module along its axial direction is connected to the support component in the vertical direction, and the other end is spaced apart from the lifting component; the inner circumferential surface of the second positioning turntable is threadedly connected to the outer circumferential surface of the second positioning module; the inner circumferential surface of the second positioning module is connected to the second lifting rod; the outer diameter of the second positioning module gradually decreases from the end away from the support component to the end close to the support component.

4. The aircraft tail fin bracket according to claim 3, characterized in that, The first positioning module includes a first connecting part and a plurality of first clamping parts; one end of the first clamping part along its axial direction is fixedly connected to one end of the first connecting part, and the other end is spaced apart from the lifting component; two adjacent first clamping parts are evenly spaced along the circumference of the first connecting part; the plurality of first clamping parts together form a first clamping area; the first lifting rod passes through the first clamping area and abuts against the first clamping part; The diameter of the first locking portion gradually decreases from the end away from the first connecting portion to the end near the first connecting portion; the end of the first connecting portion away from the first locking portion is connected to the support assembly. The second positioning module includes a second connecting part and a plurality of second clamping parts; one end of the second clamping part along its axial direction is fixedly connected to one end of the second connecting part, and the other end is spaced apart from the lifting component; two adjacent second clamping parts are evenly spaced along the circumference of the second connecting part; the plurality of second clamping parts together form a second clamping area; the second lifting rod passes through the second clamping area and abuts against the second clamping part; the diameter of the second clamping part gradually decreases from the end away from the second connecting part to the end close to the second connecting part; the end of the second connecting part away from the second clamping part is connected to the support component.

5. The aircraft tail fin bracket according to claim 4, characterized in that, The lifting assembly includes a third connecting part, multiple support plates, and a lifting plate; one end of each support plate along the height direction is connected to the lifting plate, and the other end is connected to the third connecting part; adjacent support plates are spaced apart; the end of the third connecting part away from the support plate is connected to the solenoid, the first lifting rod, and the second lifting rod.

6. The aircraft tail fin bracket according to claim 5, characterized in that, The distance between the end face of the lifting plate near the second connecting part and the second connecting part gradually decreases from both ends toward the middle.

7. The aircraft tail fin bracket according to claim 6, characterized in that, The thickness of the support plate gradually increases from both ends of the support plate to the middle of the support plate.

8. The aircraft tail fin bracket according to claim 7, characterized in that, The lifting assembly also includes multiple soft pads; the soft pads are fixedly connected to the end of the lifting plate away from the second connecting part.

9. The aircraft tail fin bracket according to claim 8, characterized in that, The thickness of the soft pad gradually decreases from both ends of the support plate to near the middle of the support plate.

10. An aircraft tail fin bracket according to claim 9, characterized in that, The support assembly includes a support frame, multiple casters, and multiple adjustable feet. The support frame includes a support base plate, a first support tube, a second support tube, and a support seat. One end of the support base plate in the vertical direction is connected to the fixed end of the caster, and the other end is connected to one end of the first support tube and one end of the second support tube in the axial direction. The adjustable feet are threadedly connected to the support base plate. The support seat is fixedly connected to the end of the support base plate away from the caster. The first connecting part is connected to the end of the first support tube away from the caster. The second connecting part is connected to the end of the second support tube away from the caster. The support seat is rotatably connected to the drive rod. The support seat is rotatably connected to the end of the lead screw away from the third connecting part.

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