An integral disassembly and assembly device for aircraft main landing gear

Abstract

The utility model relates to the technical field of aircraft assembly auxiliary devices, and specifically to an integral disassembly and assembly device for the main landing gear of an aircraft, including a disassembly and assembly device. By setting supporting positioning parts, card slots, fixing bolts, support columns and support piers, in order to avoid the main landing gear from shaking during disassembly and transportation, the aircraft main landing gear disassembly and assembly vehicle can be effectively prevented from shaking during operation, thereby improving the working stability of the aircraft main landing gear disassembly and assembly vehicle and ensuring that the aircraft main landing gear disassembly and assembly vehicle does not shake at all; then, the rotating frame is driven to a suitable position by the second telescopic rod, the work surface is straightened to a suitable height, and the disassembly and assembly device is used to lock it, and then the bottom plate is adjusted and positioned in the horizontal direction for subsequent work.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft assembly auxiliary devices, in particular to an integral disassembly and assembly device for an aircraft main landing gear. Background Art

[0002] With the rise of the aviation transportation industry, aircraft installation and maintenance has become an emerging and rapidly developing industry, and the disassembly and assembly of the aircraft main landing gear is inevitably involved in the maintenance process. When installing the main landing gear, the landing gear should be vertically upwards first, and after the connection between the main landing gear and the wing reaches the vertical installation position, the main landing gear should be rotated horizontally 90 degrees before the main landing gear and the wing can be installed; when removing the main landing gear, the main landing gear needs to be rotated 90 degrees first, and then the main landing gear is vertically downwards to separate it from the wing. The overall weight of the aircraft's main landing gear is heavy, about 200 kilograms or more (its actual weight is proportional to the weight of the aircraft), and the main landing gear is an important guarantee for the safe landing of the aircraft. The strength requirements of its connection with the wing are particularly high, so the outer dimensions of the connection between the main landing gear and the wing are large and heavy, which causes the center of gravity of the entire main landing gear.

[0003] A Chinese patent discloses an integral disassembly and assembly device for the main landing gear of the A330 aircraft (authorization announcement number CN 108313326B). This patented technology can disassemble and install the main landing gear of the A330 aircraft as a whole while ensuring safety, meeting specific needs and saving man-hours and equipment. However, the frame structure of the device is difficult to move in all directions and the posture adjustment is inconvenient, which not only increases the labor intensity and reduces the labor efficiency, but also greatly increases the risk factor of the workers' work.

[0004] Therefore, those skilled in the art provide an integral disassembly and assembly device for the main landing gear of an aircraft to solve the problems raised in the above-mentioned background technology. Utility Model Content

[0005] In order to solve the above technical problems, the utility model provides an integral disassembly and assembly device for the main landing gear of an aircraft, including a disassembly and assembly device, a bottom plate is arranged at the bottom of the disassembly and assembly device, universal wheels are arranged at the four corners of the lower end of the bottom plate, support positioning pieces are clamped at the four corners of the bottom plate, a clamping slot is arranged inside the support positioning piece, a fixing bolt is arranged on the support positioning piece, a support column is arranged at the bottom of the support positioning piece, a support pier is arranged at the bottom of the support column, a positioning part 1 is arranged at the upper end of the bottom plate, a supporting inclined plate is fastened on the positioning part 1, a fixing block 1 is arranged on the supporting inclined plate, a hydraulic rod is arranged on the fixing block 1, a connecting frame is arranged at the end of the supporting inclined plate, a slide groove is arranged inside the connecting frame, a telescopic rod 1 is fixed inside the slide groove, a slider is arranged at the end of the telescopic rod 1, a supporting frame is arranged at the top of the slider, and a telescopic rod 2 is arranged between the supporting frame and the rotating frame.

[0006] Preferably, a controller is arranged at the front of the base plate, and a connection frame is arranged at the right side of the base plate. A rotating shaft is fixed inside the connection frame, and a connection ring is rotatably arranged on the rotating shaft. A pull rod is fixed on the connection ring, and the number of the pull rods is several and can be arranged as required.

[0007] Preferably: a pull ring is provided on the top of the connecting ring, and a positioning part 2 is provided on the upper end of the bottom plate. The positioning part 1 and the positioning part 2 are symmetrically arranged, and the number of the supporting inclined plates is four, which can be arranged as needed. A fastener 1 is provided on the supporting inclined plate and the positioning part 1 and the positioning part 2, and a fixed block 2 is provided on the other supporting inclined plate. The left side of the telescopic rod 1 is fixed on the fixed block 1, and the right side is fixed on the fixed block 2. Under the action of the hydraulic rod, the lifting and telescopic settings of the four supporting inclined plates are realized. Connecting blocks are provided on both sides of the supporting frame, and a connecting rod is rotatably provided on the connecting block, and a fastener 2 is provided at the connection between the connecting rod and the connecting block. A rotating limited position frame is provided on the connecting rod, and fixed blocks 3 are provided on both sides of the supporting frame, and fasteners 3 are provided at the fixed block 3 and the supporting frame for fastening and connection. A rotating frame is provided on the top of the fixed block 3, and fasteners 4 are provided at the rotating frame and the limiting frame for fastening.

[0008] Technical effects and advantages of the utility model:

[0009] The utility model can move the disassembly and assembly device to the position where it is needed by means of the universal wheels, and the supporting positioning pieces, the card slots, the fixing bolts, the supporting columns and the supporting piers are provided, so as to prevent the main landing gear from shaking during the disassembly and assembly and transportation, and can effectively prevent the aircraft main landing gear disassembly and assembly vehicle from shaking during the working process, thereby improving the working stability of the aircraft main landing gear disassembly and assembly vehicle and ensuring that the aircraft main landing gear disassembly and assembly vehicle has no shaking; then, the rotating frame is driven to the appropriate position by the second telescopic rod, the working table is straightened to the appropriate height, and the disassembly and assembly device is locked, and then the bottom plate is adjusted and positioned in the horizontal direction for subsequent work. The aircraft main landing gear disassembly and assembly vehicle provided by the embodiment of the utility model has a simple structure and is easy to operate, and can move in all directions on a plane, so that the disassembly and assembly of the landing gear is more time-saving and labor-saving, and the cost is reduced, and the risk factor of human work is reduced. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] Figure 1 This is a schematic diagram of the structure of an aircraft main landing gear integral disassembly and assembly device provided in an embodiment of the present application. Figure 1 ;

[0011] Figure 2 This is a schematic diagram of the structure of an aircraft main landing gear integral disassembly and assembly device provided in an embodiment of the present application. Figure 2 ;

[0012] Figure 3It is a structural schematic diagram of a connection frame in an integral disassembly and assembly device for an aircraft main landing gear provided in an embodiment of the present application;

[0013] Figure 4 It is a structural schematic diagram of a support frame, a connecting block, a connecting rod, a second fastener, a limit frame, a third fixing block, a third fastener, a rotating frame, a second telescopic rod and a fourth fastener in an integral disassembly and assembly device for an aircraft main landing gear provided by an embodiment of the present application;

[0014] Figure 5 It is a structural schematic diagram of a supporting positioning member, a clamping slot, a fixing bolt, a supporting column and a supporting pier in an integral disassembly and assembly device of an aircraft main landing gear provided in an embodiment of the present application;

[0015] Figure 6 It is a structural schematic diagram of a connecting frame, a rotating shaft, a connecting ring, a pull rod and a pull ring in an integral disassembly and assembly device of an aircraft main landing gear provided in an embodiment of the present application;

[0016] Figure 7 This is a device for disassembling and assembling the main landing gear of an aircraft provided in an embodiment of the present application. Figure 3 The structural diagram at A in the middle;

[0017] Figure 8 This is a device for disassembling and assembling the main landing gear of an aircraft provided in an embodiment of the present application. Figure 2 Schematic diagram of the structure at B in the figure.

[0018] In the figure: 1. disassembly and assembly device; 2. bottom plate; 3. universal wheel; 4. controller; 5. support positioning member; 6. slot; 7. fixing bolt; 8. support column; 9. support pier; 10. connection frame; 11. rotating shaft; 12. connecting ring; 13. pull rod; 14. pull ring; 15. positioning part one; 16. supporting inclined plate; 17. positioning part two; 18. fastener one; 19. fixing block one; 20. hydraulic rod; 21. fixing block two; 22. connecting frame; 23. slide groove; 24. telescopic rod one; 25. slider; 26. support frame; 27. connecting block; 28. connecting rod; 29. ​​fastener two; 30. limit frame; 31. fixing block three; 32. fastener three; 33. rotating frame; 34. telescopic rod two; 35. fastener four. DETAILED DESCRIPTION

[0019] The present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. The embodiments of the present invention are provided for the purpose of illustration and description, and are not intended to be exhaustive or to limit the present invention to the disclosed forms. Many modifications and variations are obvious to those of ordinary skill in the art. The embodiments are selected and described in order to better illustrate the principles and practical applications of the present invention, and to enable those of ordinary skill in the art to understand the present invention and thereby design various embodiments with various modifications suitable for specific purposes. Example 1

[0020] See also Figures 1 to 8 In this embodiment, a main landing gear disassembly and assembly device for an aircraft is provided, including a disassembly and assembly device 1, a bottom plate 2 is arranged at the bottom of the disassembly and assembly device 1, universal wheels 3 are arranged at the four corners of the lower end of the bottom plate 2, a controller 4 is arranged at the front of the bottom plate 2, support positioning members 5 are clamped at the four corners of the bottom plate 2, a card slot 6 is arranged inside the support positioning member 5, a fixing bolt 7 is arranged on the support positioning member 5, a support column 8 is arranged at the bottom of the support positioning member 5, a support pier 9 is arranged at the bottom of the support column 8, a connecting frame 10 is arranged on the right side of the bottom plate 2, a rotating shaft 11 is fixed inside the connecting frame 10, a connecting ring 12 is rotatably arranged on the rotating shaft 11, a pull rod 13 is fixed on the connecting ring 12, and the number of the pull rods 13 is It can be set as needed, a pull ring 14 is set on the top of the connecting ring 12, a positioning part 15 is set on the upper end of the bottom plate 2, a supporting inclined plate 16 is fastened on the positioning part 15, and a positioning part 2 17 is set on the upper end of the bottom plate 2. The positioning part 15 and the positioning part 2 17 are symmetrically arranged, and the number of the supporting inclined plates 16 is four, which can be set as needed. A fastener 18 is set on the supporting inclined plate 16 and the positioning part 1 and the positioning part 2. A fixing block 19 is set on the supporting inclined plate 16, and a hydraulic rod 20 is set on the fixing block 19. A fixing block 21 is set on another supporting inclined plate 16. The left side of the telescopic rod 24 is fixed on the fixing block 19, and the right side is fixed On the fixed block 21, under the action of the hydraulic rod 20, the lifting and telescopic settings of the four supporting inclined plates 16 are realized. A connecting frame 22 is set at the end of the supporting inclined plate 16, and a slide groove 23 is set inside the connecting frame 22. A telescopic rod 24 is fixed inside the slide groove 23. A slider 25 is set at the end of the telescopic rod 24. A support frame 26 is set on the top of the slider 25. Connecting blocks 27 are set on both sides of the support frame 26. A connecting rod 28 is rotatably set on the connecting block 27. A fastener 29 is set at the connection between the connecting rod 28 and the connecting block 27. A limited position frame 30 is rotated on the connecting rod 28. Fixed blocks 31 are set on both sides of the support frame 26. The fixed block 31 and the support frame 2 A fastener three 32 is provided at 6 for fastening connection, a rotating frame 33 is provided at the top of the fixed block three 31, and a fastener four 35 is provided at the rotating frame 33 and the limit frame 30 for fastening, and a telescopic rod two 34 is provided between the support frame 26 and the rotating frame 33. When the telescopic rod two 34 moves, the movement of the rotating frame 33 is driven. In the specific implementation process, the support positioning member 5, the card slot 6, the fixing bolt 7, the support column 8 and the support pier 9 are provided to prevent the main landing gear from shaking during the disassembly and transportation process, which can effectively prevent the aircraft main landing gear disassembly and assembly vehicle from shaking during the work process, thereby improving the working stability of the aircraft main landing gear disassembly and assembly vehicle;

[0021] The second telescopic rod 34, the support frame 26, the connecting block 27, the connecting rod 28, the second fastener 29, the limit frame 30, the third fixing block 31, the third fastener 32 and the rotating frame 33 can effectively prevent the landing gear from tipping over and injuring the staff and causing damage to the landing gear during the process of disassembling and transporting the main landing gear of the aircraft;

[0022] When in use, the disassembly and assembly device 1 can be moved to a position where it needs to be used by first using the universal wheel 3. In the specific implementation process, there are many types of telescopic rods 24, 34 and hydraulic rods 20. In a further implementation scheme, the telescopic rod 24, 34 and hydraulic rod 20 used in the embodiment of the utility model drive the two sets of support inclined plates 16 to move during the telescopic process. Under the action of the hydraulic rod 20, the lifting and telescopic settings of the four support inclined plates 16 are realized. Of course, other methods can also be used, which are not limited here.

[0023] In addition, during the use of the utility model, after the work surface rises to the use height, the support frame 26 can be moved left and right by adjusting the telescopic rod 24 to prevent it from sliding outwards, thereby ensuring the stability of the work surface;

[0024] In the specific implementation process, in order to facilitate the adjustment of the position of the aircraft main landing gear disassembly and assembly vehicle, in a further implementation scheme, a pull ring 14 is further provided on the aircraft main landing gear disassembly and assembly vehicle described in the embodiment of the utility model. Before use, check whether there are foreign objects in the key parts of the aircraft main landing gear disassembly and assembly vehicle; check whether the hydraulic rod 20, the telescopic rod 1 24 and the telescopic rod 2 34 are operating normally; check whether each universal wheel 3 is stable, without looseness or damage; when in use, pull the aircraft main landing gear disassembly and assembly device 1 to the use position, pull the pull rod 13, adjust the working position, The supporting positioning member 5 is provided to ensure that the aircraft main landing gear disassembly and assembly vehicle does not have any shaking; then the rotating frame 33 is driven to a suitable position by the telescopic rod 2 34, the work table is straightened to a suitable height, and the disassembly and assembly device 1 is used to lock it; then the bottom plate 2 is adjusted and positioned in the horizontal direction for subsequent work. The aircraft main landing gear disassembly and assembly vehicle provided by the embodiment of the utility model has a simple structure and is easy to operate. It can move in all directions on a plane, making the disassembly and assembly of the landing gear more time-saving and labor-saving, reducing costs, and reducing the risk factor of manual work.

[0025] Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field and related fields without creative work should fall within the scope of protection of the present invention. Structures, devices and operating methods not specifically described and explained in the present invention shall be implemented according to conventional means in the field unless otherwise specified and limited.

Claims

1. An integral disassembly and assembly device for an aircraft main landing gear, characterized in that: The disassembly and assembly device (1) comprises a bottom plate (2) provided at the bottom of the disassembly and assembly device (1), universal wheels (3) provided at the four corners of the lower end of the bottom plate (2), support positioning members (5) provided at the four corners of the bottom plate (2), a card slot (6) provided inside the support positioning member (5), a fixing bolt (7) provided on the support positioning member (5), a support column (8) provided at the bottom of the support positioning member (5), a support pier (9) provided at the bottom of the support column (8), a positioning portion (15) provided at the upper end of the bottom plate (2), a support inclined plate (15) fastened to the positioning portion (15) (16), a fixing block (19) is arranged on the supporting inclined plate (16), a hydraulic rod (20) is arranged on the fixing block (19), a connecting frame (22) is arranged at the end of the supporting inclined plate (16), a slide groove (23) is arranged inside the connecting frame (22), a telescopic rod (24) is fixed inside the slide groove (23), a sliding block (25) is arranged at the end of the telescopic rod (24), a supporting frame (26) is arranged on the top of the sliding block (25), and a telescopic rod (34) is arranged between the supporting frame (26) and the rotating frame (33).

2. The aircraft main landing gear integral disassembly and assembly device according to claim 1, characterized in that: A controller (4) is arranged at the front of the base plate (2), and a connection frame (10) is arranged at the right side of the base plate (2).

3. The aircraft main landing gear integral disassembly and assembly device according to claim 2, characterized in that: A rotating shaft (11) is fixed inside the connecting frame (10), and a connecting ring (12) is rotatably arranged on the rotating shaft (11).

4. The aircraft main landing gear integral disassembly and assembly device according to claim 3, characterized in that: A pull rod (13) is fixed on the connecting ring (12), and the number of the pull rods (13) is several and can be arranged as required.

5. The aircraft main landing gear integral disassembly and assembly device according to claim 3, characterized in that: A pull ring (14) is provided at the top of the connecting ring (12), and a second positioning portion (17) is provided at the upper end of the bottom plate (2).

6. The aircraft main landing gear integral disassembly and assembly device according to claim 1, characterized in that: The first positioning portion (15) and the second positioning portion (17) are arranged symmetrically with each other, and the number of the supporting inclined plates (16) arranged is four, which can be arranged as required.

7. The aircraft main landing gear integral disassembly and assembly device according to claim 1, characterized in that: The supporting inclined plate (16) and the positioning members 1 and 2 are provided with a fastener 1 (18), and the other supporting inclined plate (16) is provided with a fixing block 2 (21). The left side of the telescopic rod 1 (24) is fixed to the fixing block 1 (19), and the right side is fixed to the fixing block 2 (21).

8. The aircraft main landing gear integral disassembly and assembly device according to claim 1, characterized in that: Connecting blocks (27) are provided on both sides of the support frame (26), a connecting rod (28) is rotatably provided on the connecting block (27), and a second fastener (29) is provided at the connection between the connecting rod (28) and the connecting block (27).

9. The aircraft main landing gear integral disassembly and assembly device according to claim 8, characterized in that: The link rod (28) is provided with a rotation limit frame (30), and two sides of the support frame (26) are provided with fixing blocks (31), and fasteners (32) are provided at the fixing blocks (31) and the support frame (26) for fastening connection.

10. The aircraft main landing gear integral disassembly and assembly device according to claim 9, characterized in that: A rotating frame (33) is provided on the top of the fixing block three (31), and fasteners four (35) are provided at the rotating frame (33) and the limiting frame (30) for fastening.

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