A universal aircraft tire belt rotating device

Abstract

The utility model provides a universal aircraft tire belt rotation device, including a symmetrically arranged mounting seat, a bearing seat fixedly installed on the top of the mounting seat, a driving shaft rotatably installed between the bearing seats, a driving inner core installed on the driving shaft through a first key, a symmetrically arranged driving skeleton installed on the outside of the driving inner core, and threaded rings nested on the two outer end faces of adjacent driving skeletons; a vulcanized rubber is provided on the outer surface of the driving skeleton; a pulley is installed on the end of the driving shaft through a second key. This device can be used to drive and rotate the aircraft wheel during the inspection and maintenance of the aircraft wheel. It adopts a modular detachable structure and a friction transmission method to realize the synchronous rotation of the aircraft wheel; and it adopts an arc structure, which can well adapt to aircraft wheels of different sizes and models, thereby enhancing its adaptability.

Description

Technical Field

[0001] The utility model belongs to the field of aviation support equipment manufacturing, and in particular relates to a universal aircraft tire belt rotating device. Background Art

[0002] During the inspection and maintenance of aircraft wheels, the wheels need to be rotated. Since the wheels themselves have no power, they need to be driven by a wheel belt rotation device. Moreover, different types of aircraft have different wheel models, so it is also necessary to ensure that the wheel belt rotation device can adapt to different sizes and models. Utility Model Content

[0003] The purpose of the utility model is to provide a universal aircraft tire belt rotation device, which can be used to drive the aircraft wheel to rotate during the aircraft wheel maintenance process. It adopts a modular detachable structure and a friction transmission method to achieve synchronous rotation of the aircraft wheel; and adopts an arc structure, which can well adapt to aircraft wheels of different sizes and models, thereby enhancing its adaptability.

[0004] In order to realize the above-mentioned technical features, the purpose of the utility model is achieved as follows: a universal aircraft tire belt rotation device, including a symmetrically arranged mounting seat, a bearing seat is fixedly installed on the top of the mounting seat, a driving shaft is rotatably installed between the bearing seats, a driving inner core is installed on the driving shaft through a first key, a symmetrically arranged driving skeleton is installed on the outside of the driving inner core, and threaded rings are nested on two outer end faces of adjacent driving skeletons; the outer surface of the driving skeleton is provided with vulcanized rubber; the end of the driving shaft is installed with a pulley through a second key.

[0005] The bearing seat is provided with an oil filling hole for oil filling.

[0006] The driving shaft is processed with a shaft ring for limiting the end of the driving inner core, and a hexagonal column is arranged on the outer side of the shaft ring;

[0007] The middle shaft section of the driving shaft is processed with a first keyway for matching with the first key, and the end of the first keyway is provided with a first thread section;

[0008] The end shaft section of the driving shaft is processed with a second keyway for matching with the second key, and the end portion of the second keyway is provided with a second threaded section.

[0009] The driving inner core is positioned and installed on the driving shaft through a first locking nut, and the first locking nut and the first threaded section form a threaded fit.

[0010] The outer end of the pulley is positioned and installed on the driving shaft through a second locking nut, and the second locking nut and the second threaded section form a threaded fit.

[0011] A center hole is processed at the center of the driving inner core, and the center hole matches with the driving shaft. A third keyway is processed on the inner wall where the center hole is located, and the third keyway matches with the first key to transmit torque;

[0012] The outer wall of the driving inner core is symmetrically processed with a first rectangular groove and a second rectangular groove.

[0013] The outer cylindrical surface of the driving skeleton adopts an arc-shaped matching surface, and a dovetail groove arranged along the longitudinal direction of the arc surface is processed on the arc-shaped matching surface;

[0014] The inner center of the driving frame is provided with a mounting cavity, the mounting cavity matches with the driving inner core, the middle part of the mounting cavity is provided with a rectangular block, the rectangular block matches with the first rectangular groove or the second rectangular groove on the driving inner core, and transmits torque;

[0015] The outer end surface of the driving skeleton is processed with a thread groove for matching with the thread ring.

[0016] The outer edge of the portion where the thread groove is located is processed with a limiting groove, and the limiting groove cooperates with the limiting block.

[0017] The vulcanized rubber is embedded in the dovetail groove after vulcanization.

[0018] The thread circles on both sides adopt positive and negative thread circles.

[0019] The utility model has the following beneficial effects:

[0020] 1. The device of the utility model can be used to drive the wheels to rotate during the wheel maintenance process of an aircraft. It adopts a modular detachable structure and a friction transmission method to achieve synchronous rotation of the wheels. Moreover, it adopts an arc structure and can well adapt to wheels of different sizes and models, thereby enhancing its adaptability.

[0021] 2. By setting the above-mentioned oil filling holes, it is ensured that the bearing seat is regularly filled with oil, thereby achieving the purpose of lubrication and extending the life of the bearing seat.

[0022] 3. The hexagonal column makes it easy to drive the drive shaft to rotate using a wrench.

[0023] 4. The power of the driving shaft can be transmitted to the driving frame through the driving inner core, and then the vulcanized rubber on the outer surface of the driving frame contacts the outer surface of the aircraft wheel to drive the aircraft wheel to rotate through friction transmission.

[0024] 5. The arrangement of the dovetail groove ensures that the vulcanized rubber and the driving frame can be reliably bonded during the subsequent vulcanization process to prevent them from falling off.

[0025] 5. The above-mentioned limiting groove facilitates the subsequent installation of the limiting block to achieve locking between the thread ring and the driving frame. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] The utility model is further described below in conjunction with the accompanying drawings and embodiments.

[0027] Figure 1 This is a three-dimensional diagram of the utility model from the first perspective.

[0028] Figure 2 This is a three-dimensional diagram from the second viewing angle of the present invention.

[0029] Figure 3 It is the front view of the utility model.

[0030] Figure 4 It is a side view of the utility model.

[0031] Figure 5 For this utility model Figure 4 Medium AA view.

[0032] Figure 6 For this utility model Figure 5 Medium BB view.

[0033] Figure 7 This is a three-dimensional diagram of the drive shaft of the utility model.

[0034] Figure 8 This is a three-dimensional diagram of the driving core of the utility model from the first perspective.

[0035] Fig. 9 This is a three-dimensional diagram of the driving inner core of the utility model from the second perspective.

[0036] Fig.10 This is a three-dimensional diagram of the first-person perspective of the driving skeleton of the utility model.

[0037] Fig.11 This is a three-dimensional diagram of the second perspective of the driving skeleton of the utility model.

[0038] Fig.12 This is a schematic diagram of the utility model device being adapted to different wheels.

[0039] Fig.13 The figure is a schematic diagram of the cooperation between the device of the utility model and the wheel drive.

[0040] In the figure: mounting seat 1, bearing seat 2, driving shaft 3, vulcanized rubber 4, pulley 5, second locking nut 6, dovetail groove 7, thread ring 8, driving inner core 9, first locking nut 10, driving skeleton 11, second key 12, first key 13, oil filling hole 14;

[0041] Hexagonal column 301, shaft collar 302, first keyway 303, first thread segment 304, second keyway 305, second thread segment 306;

[0042] Center hole 901, third keyway 902, first rectangular slot 903, second rectangular slot 904;

[0043] Thread groove 1101 , limiting groove 1102 , arc-shaped matching surface 1103 , installation cavity 1104 , rectangular block 1105 . DETAILED DESCRIPTION

[0044] The embodiments of the present utility model are further described below in conjunction with the accompanying drawings.

[0045] See also Figure 1-11 A universal aircraft tire belt rotating device comprises a symmetrically arranged mounting seat 1, a bearing seat 2 is fixedly installed on the top of the mounting seat 1, a driving shaft 3 is rotatably installed between the bearing seats 2, a driving inner core 9 is mounted on the driving shaft 3 through a first key 13, a symmetrically arranged driving skeleton 11 is installed on the outside of the driving inner core 9, and threaded rings 8 are nested and installed on the two outer end faces of the adjacent driving skeletons 11; a vulcanized rubber 4 is arranged on the outer surface of the driving skeleton 11; and a pulley 5 is mounted on the end of the driving shaft 3 through a second key 12. The above-mentioned aircraft tire belt rotating device can be used for the rotation operation during the aircraft wheel maintenance process. In the specific working process, the belt is driven by the active pulley, and the pulley 5 is synchronously driven by the belt, and then the driving shaft 3 is driven by the pulley 5, and the driving inner core 9 is driven by the driving shaft 3, and the driving skeleton 11 is driven by the driving inner core 9, and the vulcanized rubber 4 is synchronously driven by the driving skeleton 11, and the vulcanized rubber 4 is contacted with the outer surface of the aircraft tire, thereby generating friction and synchronously driving the aircraft wheel to rotate.

[0046] Furthermore, an oil injection hole 14 for oil injection is provided on the bearing seat 2. By providing the oil injection hole 14, it is ensured that the bearing seat 2 is regularly injected with oil, thereby achieving the purpose of lubrication and extending the life of the bearing seat 2.

[0047] Furthermore, the drive shaft 3 is processed with a collar 302 for limiting the end of the drive inner core 9, and a hexagonal column 301 is arranged on the outer side of the collar 302; the collar 302 can be used to position the end of the drive inner core 9 so that it can be reliably positioned and installed on the drive shaft 3. The hexagonal column 301 makes it easy to drive the drive shaft 3 to rotate by a wrench.

[0048] Furthermore, the middle shaft section of the drive shaft 3 is processed with a first keyway 303 for cooperating with the first key 13, and the end portion of the first keyway 303 is provided with a first threaded section 304; through the above-mentioned key cooperation, it is ensured that the drive shaft 3 can normally drive the drive inner core 9 to rotate.

[0049] Furthermore, the end shaft section of the driving shaft 3 is processed with a second keyway 305 for matching with the second key 12, and the end of the second keyway 305 is provided with a second threaded section 306. Through the above-mentioned key matching, it is ensured that the pulley 5 can drive the driving shaft 3.

[0050] Furthermore, the driving core 9 is positioned and installed on the driving shaft 3 through the first locking nut 10, and the first locking nut 10 forms a threaded fit with the first threaded section 304. The driving core 9 can be locked and fixed by the first locking nut 10.

[0051] Furthermore, the outer end of the pulley 5 is positioned and mounted on the drive shaft 3 through a second locking nut 6, and the second locking nut 6 is threadedly matched with the second threaded section 306. The pulley 5 can be locked and fixed by the second locking nut 6.

[0052] Furthermore, a center hole 901 is processed at the center of the driving inner core 9, and the center hole 901 matches with the driving shaft 3. A third keyway 902 is processed on the inner wall where the center hole 901 is located, and the third keyway 902 matches with the first key 13 and transmits torque; a first rectangular groove 903 and a second rectangular groove 904 are symmetrically processed on the outer wall of the driving inner core 9. The driving inner core 9 can transmit the power of the driving shaft 3 to the driving skeleton 11, and then the vulcanized rubber 4 on the outer surface of the driving skeleton 11 contacts with the outer surface of the aircraft wheel, so as to drive the aircraft wheel to rotate through friction transmission.

[0053] Furthermore, the outer circumferential surface of the driving skeleton 11 adopts an arc-shaped mating surface 1103, and a dovetail groove 7 arranged along the arc surface is processed on the arc-shaped mating surface 1103. Through the arrangement of the dovetail groove 7, the vulcanized rubber 4 and the driving skeleton 11 can be reliably bonded during the subsequent vulcanization process to prevent them from falling off.

[0054] Furthermore, the inner center of the driving skeleton 11 is provided with a mounting cavity 1104, which is matched with the driving inner core 9, and the middle part of the mounting cavity 1104 is provided with a rectangular block 1105, which is matched with the first rectangular groove 903 or the second rectangular groove 904 on the driving inner core 9 and transmits torque; the outer end surface of the driving skeleton 11 is processed with a thread groove 1101 for matching with the thread ring 8. The driving skeleton 11 can be driven by the driving inner core 9 to realize rotation.

[0055] Furthermore, the outer edge of the thread groove 1101 is processed with a limit groove 1102, which cooperates with the limit block. The limit groove 1102 facilitates the subsequent installation of the limit block to achieve locking between the thread ring 8 and the driving frame 11.

[0056] Furthermore, the vulcanized rubber 4 is embedded in the dovetail groove 7 after vulcanization, thereby ensuring the bonding strength between the two.

[0057] Furthermore, the threaded rings 8 on both sides are positive and negative threaded rings, which ensure the reliability of the combination and fixation of the two driving inner cores 9.

[0058] See also Fig.12 The docking method between the wheel rotation device and the aircraft main wheel is designed as a flexible connection, and the docking interface adopts a modular design. Different drive camber modules can be designed according to the wheel tire diameter, width and tire camber parameters of the adapted aircraft model to meet the wheel rotation inspection operations of various types of fighter jets, fighter trainers and UAVs.

[0059] According to the width and camber size of the main wheel of Type 7 aircraft, the driving wheel camber module is integrated and designed into two driving skeleton modules that can be quickly disassembled and assembled, namely, driving camber module 1 suitable for the first type 3 aircraft and driving camber module 2 suitable for the second type 4 aircraft. This can ensure the contact area between the driving wheel and the wheels of different aircraft when the belt is rotating, and realize the camber interface docking assembly that adapts to different wheels.

[0060] See also Fig.13 In order to ensure that the wheel rotation device can maintain a relatively stable state during the rotation operation after docking with the aircraft tire, the relative height difference should be maintained when the wheel rotation device is docked with the aircraft wheel, so that the center of the driving wheel is located below the center of the aircraft wheel. When the wheel rotation operation is performed, the rotating wheel will exert a downward pressing friction force on the driving wheel, making the driving wheel more stable and fully rotating the wheel, reducing the impact and vibration during the rotation process, and ensuring the transmission efficiency and stability of the belt rotation.

[0061] Working process and principle of this utility model:

[0062] When the aircraft wheel needs to be inspected, first, a driving skeleton 11 with an arc-shaped mating surface 1103 of corresponding size is selected according to the size of the wheel, and then the entire aircraft tire belt rotating device is fixedly installed on the power device, and the driving wheel of the power device is connected to the pulley 5 through a belt, and then the power device is started, and the pulley 5 is synchronously driven by the belt, and then the driving shaft 3 is driven by the pulley 5, and the driving inner core 9 is driven by the driving shaft 3, and the driving skeleton 11 is driven by the driving inner core 9, and the vulcanized rubber 4 is synchronously driven by the driving skeleton 11, and the vulcanized rubber 4 contacts the outer surface of the aircraft tire, thereby generating friction and synchronously driving the aircraft wheel to rotate.

Claims

1. A universal aircraft tire belt rotation device, characterized in that: The invention comprises a symmetrically arranged mounting seat (1), a bearing seat (2) being fixedly mounted on the top of the mounting seat (1), a driving shaft (3) being rotatably mounted between the bearing seats (2), a driving inner core (9) being mounted on the driving shaft (3) in cooperation with a first key (13), a symmetrically arranged driving skeleton (11) being positioned and mounted on the outside of the driving inner core (9), and threaded rings (8) being nested and mounted on two outer end surfaces of adjacent driving skeletons (11); a vulcanized rubber (4) being provided on the outer surface of the driving skeleton (11); and a pulley (5) being mounted on the end of the driving shaft (3) in cooperation with a second key (12).

2. A universal aircraft tire belt rotation device according to claim 1, characterized in that: The bearing seat (2) is provided with an oil injection hole (14) for injecting oil.

3. The universal aircraft tire belt rotation device according to claim 1, characterized in that: The drive shaft (3) is provided with a shaft ring (302) for limiting the end position of the drive inner core (9), and a hexagonal column (301) is arranged on the outer side of the shaft ring (302); A first keyway (303) for matching with the first key (13) is machined on a middle shaft section of the driving shaft (3), and a first threaded section (304) is arranged at the end of the first keyway (303); The end shaft section of the drive shaft (3) is processed with a second keyway (305) for matching with the second key (12), and the end portion of the second keyway (305) is provided with a second threaded section (306).

4. The universal aircraft tire belt rotation device according to claim 3, characterized in that: The driving inner core (9) is positioned and mounted on the driving shaft (3) via a first locking nut (10), and the first locking nut (10) and the first threaded section (304) form a threaded fit.

5. The universal aircraft tire belt rotation device according to claim 3, characterized in that: The outer end of the pulley (5) is positioned and mounted on the drive shaft (3) via a second locking nut (6), and the second locking nut (6) and the second threaded section (306) form a threaded fit.

6. The universal aircraft tire belt rotation device according to claim 3, characterized in that: A center hole (901) is machined at the center of the driving inner core (9), the center hole (901) cooperates with the driving shaft (3), a third key groove (902) is machined on the inner wall where the center hole (901) is located, the third key groove (902) cooperates with the first key (13) and transmits torque; A first rectangular groove (903) and a second rectangular groove (904) are symmetrically processed on the outer wall of the driving inner core (9).

7. A universal aircraft tire belt rotation device according to claim 6, characterized in that: The outer cylindrical surface of the driving skeleton (11) adopts an arc-shaped mating surface (1103), and the arc-shaped mating surface (1103) is processed with a dovetail groove (7) arranged along the longitudinal direction of the arc surface; An installation cavity (1104) is provided at the inner center of the driving skeleton (11), the installation cavity (1104) cooperates with the driving inner core (9), a rectangular block (1105) is provided at the middle of the installation cavity (1104), the rectangular block (1105) cooperates with the first rectangular groove (903) or the second rectangular groove (904) on the driving inner core (9) and transmits torque; The outer end surface of the driving skeleton (11) is processed with a thread groove (1101) for matching with the thread ring (8).

8. The universal aircraft tire belt rotation device according to claim 7, characterized in that: A limiting groove (1102) is processed on the outer edge of the portion where the thread groove (1101) is located, and the limiting groove (1102) cooperates with the limiting block.

9. The universal aircraft tire belt rotation device according to claim 7, characterized in that: The vulcanized rubber (4) is embedded in the dovetail groove (7) after vulcanization.

10. The universal aircraft tire belt rotation device according to claim 7, characterized in that: The threaded circles (8) on both sides are positive and negative threaded circles.

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