An aircraft wheel lifting device for aircraft maintenance

Abstract

The present invention discloses an aircraft wheel lifting device for maintenance, including an interlaced self-locking device, a self-rotating driving member and a hydraulic lifting member. The present invention belongs to the field of aircraft wheel maintenance, and specifically refers to an aircraft wheel lifting device for maintenance; the present invention automatically bends and locks the aircraft wheel placed outside the limiting guide member through the interlaced self-locking device proposed, arranges the guide member to slide downward in the interlaced member under the action of gravity, and drags the bending self-locking structure to bend by dragging the spring, and presses the wheel hub of the aircraft wheel to self-lock, which is convenient for operators to detect the aircraft wheel. In this process, the wheel hub of the aircraft wheel is clamped and fixed by a physical structure to ensure that the aircraft wheel rotates in a balanced state, which is convenient for operators to detect, and avoids the aircraft wheel from overturning during movement, causing damage to the aircraft wheel and causing economic losses.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft wheel maintenance, and in particular relates to an aircraft wheel lifting device used for aircraft maintenance. Background Art

[0002] Generally speaking, an aircraft needs to replace its tires every 200 or so takeoffs and landings. This is because aircraft tires need to withstand faster takeoff speeds, greater impact forces, and rapid temperature changes, so their replacement criteria are mainly based on the number of takeoffs and landings, rather than mileage or usage time. During the daily maintenance of aircraft wheels, it is necessary to thoroughly check the wear of each tire while cleaning, disassembling, and assembling the aircraft wheels to ensure that the tires are evenly worn and there is no uneven wear. The tire surface should be inspected for cracks, scratches, and damage, and the tire pressure should be tested. It can be seen that in order to avoid the occurrence of safety hazards, the inspection and maintenance of aircraft wheels require multiple processes. During the inspection process, providing a stable aircraft wheel locking component can prevent the aircraft wheel from overturning due to the movement of the aircraft wheel, causing the aircraft wheel to be bumped and damaged. In order to maintain the stability of the aircraft wheel being inspected during the inspection process, all current aircraft wheel lifting devices are usually equipped with locking parts, but they have the following obvious disadvantages:

[0003] (1) The wheel hub is adsorbed by electrifying the adsorption component. However, this type of device obviously relies on power support and has certain requirements for operation scenarios, and is not suitable for multiple usage scenarios;

[0004] (2) A self-locking ring with a physical structure is used to self-lock the wheel hub. However, the bending contact point of the self-locking ring is not on the wheel hub. It can only ensure that the wheel hub will not fall, but it cannot guarantee the stability of the wheel hub. During the rotation process, the contact point of the self-locking ring on the wheel hub causes inevitable friction and collision, causing the wheel hub to be bumped and even damaging the coating on its surface. Summary of the Invention

[0005] In response to the above situation, the present invention provides an aircraft wheel lifting device for aircraft maintenance. The aircraft wheel placed outside the limiting guide member is automatically bent and locked by the proposed interlaced self-locking device. Under the action of gravity, the guide member is placed in the interlaced member to slide downward. By dragging the spring, the bending self-locking structure is dragged to bend, and the wheel hub of the aircraft wheel is pressed and self-locked. The contact ring slides into the induction area of ​​the induction ring, and the self-rotating drive member starts to operate, driving the interlaced self-locking device to rotate, making it convenient for operators to perform inspection work on the aircraft wheel.

[0006] During this process, the hub of the aircraft wheel is locked and fixed by a physical structure, and the middle position of the aircraft wheel is pressed at multiple contact points in a circular array through multiple groups of curved self-locking structures arranged in a circular shape. The uniform pressure at each contact point prevents the hub of the aircraft wheel from tilting or overturning due to differences in the amount of force applied, ensuring that the aircraft wheel rotates in a balanced state. This facilitates inspection by operators and prevents the aircraft wheel from overturning during movement, causing damage to the aircraft wheel and resulting in emergency losses.

[0007] The technical solution adopted by the present invention is as follows: The present invention proposes an aircraft wheel lifting device for aircraft maintenance, including an insertion self-locking device, a self-rotating drive component and a hydraulic lifting component. The insertion self-locking device is fixedly arranged above the self-rotating drive component, and the self-rotating drive component is fixedly connected to the hydraulic lifting component. The insertion self-locking device includes an installation guide component, a sliding self-locking component and an insertion fixing component. The installation guide component and the sliding self-locking component are inserted in the insertion fixing component, the sliding self-locking component is fixedly connected to the insertion fixing component, and the installation guide component is inserted and slides in the insertion fixing component.

[0008] Furthermore, the placement guide member includes an interpenetrating clamping member and a limiting guide member, the limiting guide member is fixedly provided at the lower end portion of the interpenetrating clamping member, the interpenetrating clamping member includes a clamping top ring, a connecting circular ring, an interpenetrating connecting column and a connecting main pipe, the clamping top ring is fixedly provided at the top outer wall of the connecting circular ring, the interpenetrating connecting column is provided with multiple branches and is fixedly provided in a circular array at the bottom of the connecting circular ring, and the top of the connecting main pipe is fixedly connected to the bottom of the interpenetrating connecting column.

[0009] Preferably, the limiting guide member includes a fan-shaped distribution guide piece, a pressing top ring, a pressing bottom plate and a guide ring. The fan-shaped distribution guide piece is provided with multiple branches and is fixedly connected to the lower end of the connecting main pipe in a circular array. The pressing top ring is fixedly connected to the top of the fan-shaped distribution guide piece. The pressing bottom plate is fixedly connected to the bottom of the fan-shaped distribution guide piece. The pressing top ring, the pressing bottom plate and the connecting main pipe are arranged concentrically. A contact ring is provided in the pressing top ring, and the contact ring is connected to the self-rotating drive member signal. The bottom of the guide ring is fixedly connected to the top of the pressing top ring, and the guide ring and the pressing top ring are arranged concentrically.

[0010] As a further preferred embodiment of the present invention, the sliding self-locking component includes a curved self-locking structure and a bottom fixed ring. The curved self-locking structure is provided with multiple groups, and the multiple groups of curved self-locking structures are fixedly provided on the top of the bottom fixed ring in a circular array. The curved self-locking structure includes a fixed bottom rod, an inclined rod, an end rod and a hinge. The bottom of the fixed bottom rod is fixed to the top of the bottom fixed ring, the lower end of the inclined rod is rotatably connected to the upper end of the fixed bottom rod, and the upper end of the inclined rod is connected to the lower end of the end rod by a hinge.

[0011] Furthermore, a side connecting rod is fixedly provided on the side of the end rod, and a counterweight block is slidably provided on the upper end of the end rod, and a drag spring is fixedly provided between the side connecting rod and the pressing top ring. The drag spring proposed in the device of the present invention connects the side connecting rod and the pressing top ring. Under normal circumstances, the initial state of the drag spring is the original state. When the pressing top ring is pressed downward by the aircraft wheel, the drag spring drags the side connecting rod, causing the end rod to tilt and deflect at an angle, and under the action of the gravity of the counterweight block, the angle of the end rod changes. Since the fixed bottom rod mainly plays a supporting role in height, with the cooperation of the hinge hinge, the tilt rod between the end rod and the fixed bottom rod is adaptively adjusted in angle, and the counterweight block presses the wheel hub, so that under the pressure of gravity, the curved self-locking structure can be autonomously and completely locked.

[0012] Preferably, the interpenetrating fixing component includes a locking bottom ring, a limiting ring, a connecting ring tube and a placement base, the locking bottom ring is fixedly connected to the outer wall of the limiting ring, the connecting ring tube is fixedly connected to the bottom of the limiting ring, and the limiting ring is vertically provided with placement openings and interpenetrating openings in a circular array. The outermost edge of the locking top ring proposed in the device of the present invention fits the inward surface of the tilting rod, the inner wall of the locking bottom ring fits the outward surface of the tilting rod, the outer wall of the locking top ring is inclined, and the inclination angle of the inner wall of the locking bottom ring is consistent. When the height of the locking top ring moves down, the angle formed between the outer edge point of the locking top ring and the lowest point of the inner wall of the locking bottom ring changes, driving the tilting rod to shift in angle, pushing the end rod to move outward.

[0013] As a further preference of the present invention, the interpenetrating connecting column is interpenetratingly arranged in the interpenetrating opening, the fixing bottom rod is fixedly arranged in the placement opening, the bottom fixing ring is fixedly arranged at the bottom of the limiting ring, the lower end of the connecting ring tube is provided with a limiting groove, the placement base is a hollow structure, the top of the placement base is provided with a fan-shaped groove, the fan-shaped distribution guide plate slides in the limiting groove and the fan-shaped groove, a compression spring is provided in the placement base, the top of the compression spring is fixedly arranged at the bottom of the pressing film, and the top of the placement base is provided with an induction ring, and the induction ring is connected to the rotating central axis signal.

[0014] Furthermore, the self-rotating driving component includes a receiving ring groove, a rotating central axis and a placement groove, the placement base is fixedly arranged in the receiving ring groove, the rotating central axis is fixedly arranged at the bottom of the receiving ring groove, and the receiving ring groove and the rotating central axis are arranged in the placement groove.

[0015] Preferably, the contact ring and the induction ring are connected to the rotating central axis signal, and when the contact ring slides into the induction range of the induction ring, the rotating central axis starts to operate. The contact ring and the induction ring proposed in the device of the present invention are both connected to the rotating central axis. When a wheel hub is placed on the placement guide member, the rotating central axis is opened autonomously, so that the aircraft wheel can be rotated while the wheel hub is self-locked, which is convenient for subsequent observation operations.

[0016] As a further preference of the present invention, the hydraulic lifting component includes a hydraulic lifting base, a lateral lifting rod and a stable base. One end of the lateral lifting rod is connected to the hydraulic lifting base, and the other end of the lateral lifting rod is fixed to the bottom of the placement groove. The stable base is fixed to the bottom of the hydraulic lifting base. The hydraulic lifting base proposed in the device of the present invention is an existing technology. Among the currently available technical means, it has the remarkable characteristics of compact structure, high safety performance, high efficiency and environmental protection. It occupies a small area and operates stably, and is easy and safe to operate.

[0017] The beneficial effects achieved by the present invention using the above structure are as follows:

[0018] (1) The drag spring proposed in the device of the present invention connects the side connecting rod and the pressing top ring. Under normal conditions, the initial state of the drag spring is the original state. When the pressing top ring is pressed downward by the aircraft wheel, the drag spring drags the side connecting rod, causing the end rod to tilt and deflect at an angle. Under the action of the gravity of the counterweight, the angle of the end rod changes. Since the fixed bottom rod mainly plays a supporting role in height, with the cooperation of the hinge, the tilt rod between the end rod and the fixed bottom rod is adaptively adjusted in angle. The counterweight presses the wheel hub, so that the curved self-locking structure can be fully locked autonomously under the pressure of gravity.

[0019] (2) The outermost edge of the engaging top ring proposed in the device of the present invention fits in with the inner surface of the tilting rod, and the inner wall of the engaging bottom ring fits in with the outer surface of the tilting rod. The outer wall of the engaging top ring is inclined, and the inclination angle is consistent with that of the inner wall of the engaging bottom ring. When the height of the engaging top ring moves down, the angle formed between the outer edge point of the engaging top ring and the lowest point of the inner wall of the engaging bottom ring changes, driving the tilting rod to shift in angle, pushing the end rod to move outward.

[0020] (3) The contact ring and the induction ring proposed in the device of the present invention are both connected to the rotating central axis. When a wheel hub is placed on the placement guide member, the rotating central axis is automatically opened, so that the aircraft wheel can be rotated while the wheel hub is self-locked, which is convenient for subsequent observation operations.

[0021] (4) The hydraulic lifting base proposed in the device of the present invention is an existing technology. Among the currently available technical means, it has the remarkable characteristics of compact structure, high safety performance, high efficiency and environmental protection, etc. It occupies a small area and operates stably, and is easy and safe to operate. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 This is a side view of an aircraft wheel lifting device for aircraft maintenance proposed by the present invention;

[0023] Figure 2 This is an elevation view of an aircraft wheel lifting device for aircraft maintenance proposed by the present invention;

[0024] Figure 3 This is a front view of the interlaced self-locking device and the self-rotating driving component proposed by the present invention;

[0025] Figure 4 for Figure 3 A cross-sectional view along the cutting line AA;

[0026] Figure 5 for Figure 4 A cross-sectional view along the cutting line BB;

[0027] Figure 6 This is a structural diagram of the sliding self-locking component proposed by the present invention;

[0028] Figure 7 This is a schematic structural diagram of the interlaced fixing member proposed in the present invention;

[0029] Figure 8 The schematic diagram of the structure of the guide member provided by the present invention is as follows Figure 1 ;

[0030] Figure 9 The schematic diagram of the structure of the guide member provided by the present invention is as follows Figure 2 .

[0031] Among them, 1. interpenetrating self-locking device, 2. self-rotating drive member, 3. hydraulic lifting member, 4. placement guide member, 5. sliding self-locking member, 6. interpenetrating fixing member, 7. receiving ring groove, 8. rotating central axis, 9. placement groove, 10. hydraulic lifting base, 11. horizontal lifting rod, 12. stable base, 13. interpenetrating clamping member, 14. limiting guide member, 15. bending self-locking structure, 16. bottom fixed ring, 17. clamping bottom ring, 18. limiting ring, 19. connecting ring pipe, 20. placement base, 2 1. Engage the top ring, 22. Connect the circular ring, 23. Insert the connecting column, 24. Connect the main pipe, 25. Fan-shaped guide plates, 26. Press the top ring, 27. Press the bottom plate, 28. Guide ring, 29. Contact ring, 30. Retain the bottom rod, 31. Tilting rod, 32. End rod, 33. Hinge, 34. Side connecting rod, 35. Counterweight, 36. Drag spring, 37. Place the opening, 38. Insert the opening, 39. Limit the slot, 40. Fan-shaped slot, 41. Compression spring, 42. Induction ring.

[0032] The accompanying drawings are used to provide further understanding of the present invention and constitute a part of the specification. They are used to explain the present invention together with the embodiments of the present invention and do not constitute a limitation of the present invention. DETAILED DESCRIPTION

[0033] 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, rather than all the embodiments; based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0034] In the description of the present invention, it should be understood that terms such as "upper", "lower", "front", "back", "left", "right", "top", "bottom", "inside" and "outside" indicating directions or positional relationships are based on the directions or positional relationships shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction. Therefore, they should not be understood as limiting the present invention.

[0035] like Figures 1-9As shown, the present invention proposes an aircraft wheel lifting device for aircraft maintenance, including an insertion self-locking device 1, a self-rotating drive member 2 and a hydraulic lifting member 3. The insertion self-locking device 1 is fixedly arranged above the self-rotating drive member 2, and the self-rotating drive member 2 is fixedly connected to the hydraulic lifting member 3. The insertion self-locking device 1 includes an installation guide member 4, a sliding self-locking member 5 and an insertion fixed member 6. The installation guide member 4 and the sliding self-locking member 5 are inserted in the insertion fixed member 6, the sliding self-locking member 5 is fixedly connected to the insertion fixed member 6, and the installation guide member 4 is inserted and slides in the insertion fixed member 6.

[0036] Among them, the placement guide member 4 includes an interpenetrating clamping member 13 and a limiting guide member 14. The limiting guide member 14 is fixedly connected to the lower end of the interpenetrating clamping member 13. The interpenetrating clamping member 13 includes a clamping top ring 21, a connecting ring 22, an interpenetrating connecting column 23 and a connecting main pipe 24. The clamping top ring 21 is fixedly connected to the top outer wall of the connecting ring 22. The interpenetrating connecting column 23 is provided with multiple branches and is fixedly connected to the bottom of the connecting ring 22 in a circular array. The top of the connecting main pipe 24 is fixed to the bottom of the interpenetrating connecting column 23.

[0037] The limiting guide member 14 includes a fan-shaped distribution guide piece 25, a pressing top ring 26, a pressing bottom plate 27 and a guide ring 28. The fan-shaped distribution guide piece 25 is provided with multiple branches and is fixedly connected to the lower end of the connecting main pipe 24 in a circular array. The pressing top ring 26 is fixedly connected to the top of the fan-shaped distribution guide piece 25. The pressing bottom plate 27 is fixedly connected to the bottom of the fan-shaped distribution guide piece 25. The pressing top ring 26, the pressing bottom plate 27 and the connecting main pipe 24 are arranged concentrically. A contact ring 29 is provided in the pressing top ring 26. The contact ring 29 is connected to the signal of the self-rotating drive member 2. The bottom of the guide ring 28 is fixedly connected to the top of the pressing top ring 26. The guide ring 28 and the pressing top ring 26 are arranged concentrically.

[0038] The sliding self-locking component 5 includes a curved self-locking structure 15 and a bottom fixed ring 16. The curved self-locking structure 15 is provided with multiple groups. The multiple groups of curved self-locking structures 15 are fixedly arranged on the top of the bottom fixed ring 16 in a circular array. The curved self-locking structure 15 includes a fixed bottom rod 30, an inclined rod 31, an end rod 32 and a hinge 33. The bottom of the fixed bottom rod 30 is fixed to the top of the bottom fixed ring 16, the lower end of the inclined rod 31 is rotatably connected to the upper end of the fixed bottom rod 30, and the upper end of the inclined rod 31 is connected to the lower end of the end rod 32 through a hinge 33.

[0039] A side connecting rod 34 is fixedly connected to the side of the end rod 32 , a counterweight 35 is slidably provided on the upper end of the end rod 32 , and a drag spring 36 is fixedly connected between the side connecting rod 34 and the pressing top ring 26 .

[0040] The interpenetrating fixing component 6 includes a locking bottom ring 17, a limiting ring 18, a connecting ring tube 19 and a placement base 20. The locking bottom ring 17 is fixedly provided on the outer wall of the limiting ring 18, and the connecting ring tube 19 is fixedly provided on the bottom of the limiting ring 18. The limiting ring 18 has placement openings 37 and interpenetrating openings 38 vertically opened in a circular array. The connecting ring tube 19 is fixedly connected to the placement base 20.

[0041] The interpenetrating connecting column 23 is inserted in the interpenetrating opening 38, the fixing bottom rod 30 is fixed in the placement opening 37, the bottom fixing ring 16 is fixed to the bottom of the limiting ring 18, and the lower end of the connecting ring tube 19 is provided with a limiting groove 39. The placement base 20 is a hollow structure, and the top of the placement base 20 is provided with a fan-shaped groove 40. The fan-shaped distribution guide piece 25 slides in the limiting groove 39 and the fan-shaped groove 40. A compression spring 41 is provided in the placement base 20, and the top of the compression spring 41 is fixed to the bottom of the pressing bottom plate 27. An induction ring 42 is provided on the top of the placement base 20.

[0042] The self-rotating driving member 2 includes a receiving ring groove 7, a rotating central axis 8 and a placement groove 9. The placement base 20 is fixedly arranged in the receiving ring groove 7. The rotating central axis 8 is fixedly arranged at the bottom of the receiving ring groove 7. The receiving ring groove 7 and the rotating central axis 8 are arranged in the placement groove 9.

[0043] The contact ring 29 and the induction ring 42 are connected to the rotating central shaft 8 by signal. When the contact ring 29 slides into the induction range of the induction ring 42, the rotating central shaft 8 starts to operate.

[0044] The hydraulic lifting component 3 includes a hydraulic lifting base 10, a lateral lifting rod 11 and a stable base 12. One end of the lateral lifting rod 11 is connected to the hydraulic lifting base 10, and the other end of the lateral lifting rod 11 is fixed to the bottom of the placement groove 9. The stable base 12 is fixed to the bottom of the hydraulic lifting base 10.

[0045] When in use, the device of the present invention is connected to a power source, the contact ring 29 and the induction ring 42 are connected to a power source, the rotating central axis 8 is connected to a power source, and the contact ring 29 and the induction ring 42 are connected to the rotating central axis 8 for signal connection.

[0046] The hub of the aircraft wheel is clamped on the interpenetrating clamping member 13, and the central hole of the hub moves downward along the guide ring 28. The hub is placed on the pressing top ring 26. Under the action of gravity, the pressing top ring 26 moves downward, and the fan-shaped distribution guide pieces 25 slide downward in the limiting grooves 39 of the connecting ring tube 19 and the fan-shaped grooves 40 of the placement base 20. The pressing bottom piece 27 squeezes the compression spring 41 in the placement base 20, and the limiting guide piece 14 moves downward as a whole, dragging the interpenetrating clamping member 13. The connecting main pipe 24 moves downward with the limiting guide piece 14, and slides in the interpenetrating opening 38 of the limiting ring 18 through the interpenetrating connecting column 23, dragging the upper connecting ring 22 and the engaging top ring 21 downward, and the engaging top ring 21 is at the bottom. During the shifting process, the tilting rod 31 is pushed to tilt outward. Under the joint action of the tilting rod 31 and the drag spring 36, the end rod 32 connected to the upper end of the tilting rod 31 tilts outward at an angle. Under the gravity of the counterweight 35, the upper end of the end rod 32 sinks, and the counterweight 35 contacts the top surface of the wheel hub. Under the joint action of multiple sets of curved self-locking structures 15, multiple counterweights 35 press the wheel hub synchronously, pressing the contact ring 29 in the top ring 26 to slide into the sensing area of ​​the induction ring 42 of the mounting base 20, and the rotating central axis 8 rotates. The rotating central axis 8 drives the receiving ring groove 7 to rotate, and the receiving ring groove 7 drives the interlaced self-locking device 1 to rotate as a whole, driving the wheel hub to rotate. According to the required detection content or the tester's own needs, the lifting height of the lateral lifting rod 11 is adjusted by hydraulic lifting base 10.

[0047] When the inspection work is completed, the wheel hub is lifted, the wheel hub stops pressing the top ring 26, and the bottom plate 27 is pressed to reset the limit guide 14 under the reset property of the compression spring 41. The interlaced engaging part 13 is reset as the limit guide 14 moves upward, and the engaging top ring 21 stops pressing against the inner wall of the tilting rod 31. The pressing top ring 26 stops dragging the drag spring 36, and the wheel hub is directly lifted. The bent self-locking structure 15 is reset under the moving contact with the inner wall of the wheel hub during the upward movement of the wheel hub, and the hinge hinge 33 ensures that the tilting rod 31 and the end rod 32 are arranged vertically.

[0048] The above is the overall workflow of the present invention. Just repeat this step next time you use it.

[0049] It should be noted that, in this document, relational terms such as first and second, etc., are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "comprises," "comprising," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that includes a list of elements includes not only those elements but also other elements not explicitly listed, or elements inherent to such process, method, article, or apparatus.

[0050] The present invention and its embodiments are described above. This description is not restrictive. The drawings show only one embodiment of the present invention, and the actual structure is not limited thereto. In short, if a person skilled in the art is inspired by this and, without departing from the purpose of the present invention, designs structures and embodiments similar to this technical solution without inventiveness, they shall fall within the scope of protection of the present invention.

Claims

1. An aircraft wheel lifting device for aircraft maintenance, characterized in that: The invention comprises an interpenetrating self-locking device (1), a self-rotating driving member (2) and a hydraulic lifting member (3), wherein the interpenetrating self-locking device (1) is fixedly arranged above the self-rotating driving member (2), the self-rotating driving member (2) is fixedly connected to the hydraulic lifting member (3), the interpenetrating self-locking device (1) comprises a placement guide member (4), a sliding self-locking member (5) and an interpenetrating fixing member (6), the placement guide member (4) and the sliding self-locking member (5) are inserted in the interpenetrating fixing member (6), the sliding self-locking member (5) and the interpenetrating fixing member (6) are interpenetrating with each other, and the interpenetrating self-locking member (5) is fixedly connected to the interpenetrating fixing member (6). The inserting and fixing member (6) is fixedly connected, the placement guide member (4) is inserted and slid in the inserting and fixing member (6), the placement guide member (4) comprises an inserting and locking member (13) and a limiting guide member (14), the limiting guide member (14) is fixedly connected to the lower end of the inserting and locking member (13), a locking top ring (21) is arranged on the top of the inserting and locking member (13), a contact ring (29) is arranged on the limiting guide member (14), and an induction ring (42) cooperating with the contact ring (26) is arranged on the inserting and fixing member (6); The sliding self-locking component (5) comprises a curved self-locking structure (15) and a bottom fixed ring (16). The curved self-locking structure (15) is provided with a plurality of groups. The plurality of groups of the curved self-locking structures (15) are fixedly arranged on the top of the bottom fixed ring (16) in a circular array. The curved self-locking structure (15) comprises a fixed bottom rod (30), an inclined rod (31), an end rod (32) and a hinge (33). The bottom of the fixed bottom rod (30) is connected to the bottom of the fixed bottom rod (30). The top of the bottom fixed ring (16) is fixed, the lower end of the tilting rod (31) is rotatably connected to the upper end of the fixed bottom rod (30), and the upper end of the tilting rod (31) is connected to the lower end of the end rod (32) via a hinge (33); A drag spring (36) is provided between the end rod (32) and the limiting guide member (14), a counterweight (35) is provided at the upper end of the end rod (32), the outer edge of the engaging top ring (21) is in contact with the inner surface of the tilting rod (31), and the outer wall of the engaging top ring (21) is inclined; When the aircraft wheel is placed on the limiting guide member (14), the weight of the aircraft wheel drives the limiting guide member (14) and the interlacing engaging member (13) to move downward, and the engaging top ring (21) on the top of the interlacing engaging member (13) moves downward accordingly, thereby pushing the tilting rod (31) to tilt outward, and the end rod (32) connected to the upper end of the tilting rod (31) tilts outward at an angle under the joint action of the tilting rod (31) and the drag spring (36), and the upper end of the end rod (32) sinks under the gravity of the counterweight (35), the counterweight (35) presses the wheel hub, and when the limiting guide member (14) moves downward to the contact ring (26) and enters the sensing range of the sensing ring (42), the self-rotating driving member (2) drives the aircraft wheel to rotate.

2. The aircraft wheel lifting device for aircraft maintenance according to claim 1, characterized in that: The insertion engaging member (13) comprises an engaging top ring (21), a connecting circular ring (22), an inserting connecting column (23) and a connecting main pipe (24); the engaging top ring (21) is fixedly connected to the top outer wall of the connecting circular ring (22); the inserting connecting column (23) is provided with a plurality of columns and is fixedly connected to the bottom of the connecting circular ring (22) in a circular array; the top of the connecting main pipe (24) is fixedly connected to the bottom of the inserting connecting column (23).

3. The aircraft wheel lifting device for aircraft maintenance according to claim 2, characterized in that: The position limiting guide member (14) comprises a fan-shaped distribution guide piece (25), a pressing top ring (26), a pressing bottom plate (27) and a guide ring (28); the fan-shaped distribution guide piece (25) is provided with a plurality of branches and is fixedly arranged in a circular array on the lower end of the connecting main pipe (24); the pressing top ring (26) is fixedly arranged on the top of the fan-shaped distribution guide piece (25); the pressing bottom plate (27) is fixedly arranged on the bottom of the fan-shaped distribution guide piece (25); the pressing top ring (26), the pressing bottom plate (27) and the connecting main pipe (24) are arranged concentrically; a contact ring (29) is provided inside the pressing top ring (26); the contact ring (29) is connected to the self-rotating driving member (2) for signal; the bottom of the guide ring (28) is fixedly arranged on the top of the pressing top ring (26); the guide ring (28) and the pressing top ring (26) are arranged concentrically.

4. The aircraft wheel lifting device for aircraft maintenance according to claim 3, characterized in that: A side connecting rod (34) is fixedly connected to the side of the end rod (32), a counterweight (35) is slidably provided at the upper end of the end rod (32), and a drag spring (36) is fixedly connected between the side connecting rod (34) and the pressing top ring (26).

5. The aircraft wheel lifting device for aircraft maintenance according to claim 4, characterized in that: The interpenetrating fixing member (6) comprises a locking bottom ring (17), a limiting ring (18), a connecting ring tube (19) and a placement base (20); the locking bottom ring (17) is fixedly connected to the outer wall of the limiting ring (18); the connecting ring tube (19) is fixedly connected to the bottom of the limiting ring (18); the limiting ring (18) has placement openings (37) and interpenetrating openings (38) vertically opened in a circumferential array; and the connecting ring tube (19) is fixedly connected to the placement base (20).

6. The aircraft wheel lifting device for aircraft maintenance according to claim 5, characterized in that: The insertion connection column (23) is inserted into the insertion opening (38), the fixing bottom rod (30) is fixedly connected to the placement opening (37), the bottom fixing ring (16) is fixedly connected to the bottom of the limiting ring (18), the lower end of the connecting ring tube (19) is provided with a limiting slot (39), the placement base (20) is a hollow structure, the top of the placement base (20) is provided with a fan-shaped slot (40), the fan-shaped distribution guide sheet (25) slides in the limiting slot (39) and the fan-shaped slot (40), the placement base (20) is provided with a compression spring (41), the top of the compression spring (41) is fixedly connected to the bottom of the pressing bottom sheet (27), and the top of the placement base (20) is provided with an induction ring (42).

7. The aircraft wheel lifting device for aircraft maintenance according to claim 6, characterized in that: The self-rotating driving member (2) comprises a receiving ring groove (7), a rotating central axis (8) and a placement groove (9); the placement base (20) is fixedly arranged in the receiving ring groove (7); the rotating central axis (8) is fixedly arranged at the bottom of the receiving ring groove (7); and the receiving ring groove (7) and the rotating central axis (8) are arranged in the placement groove (9).

8. The aircraft wheel lifting device for aircraft maintenance according to claim 7, characterized in that: The contact ring (29) and the induction ring (42) are connected to the rotating central shaft (8) by signal, and when the contact ring (29) slides into the induction range of the induction ring (42), the rotating central shaft (8) starts to operate.

9. The aircraft wheel lifting device for aircraft maintenance according to claim 8, characterized in that: The hydraulic lifting component (3) comprises a hydraulic lifting base (10), a lateral lifting rod (11) and a stabilizing base (12); one end of the lateral lifting rod (11) is connected to the hydraulic lifting base (10), the other end of the lateral lifting rod (11) is fixedly connected to the bottom of the placement groove (9), and the stabilizing base (12) is fixedly connected to the bottom of the hydraulic lifting base (10).

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