Aircraft wheel accessory disassembly device and disassembly method

Abstract

A device and method for disassembling an aircraft wheel accessory. The disassembly device comprises a central shaft and an accessory clamping mechanism. The central shaft is a rigid screw structure. A compression joint is provided at the lower end of the rigid screw. A first handle is provided at the upper end of the central screw. The accessory clamping mechanism comprises a nut sleeve, a lug nut, a lug ring, multiple claw angles, and multiple connecting rod assemblies. The nut sleeve is a double-sided internal and external threaded structure. Its internal thread is connected to the external thread of the rigid screw, and its external thread is connected to the internal thread of the lug nut. The outer side of the lug ring radiates The shaped ear piece is hinged to the top of a claw angle, the upper end of each connecting rod assembly is hinged to a radial ear piece of the lug nut, and the two side links of each connecting rod assembly are respectively hinged to the middle parts of two adjacent claw angles. The middle parts of all claw angles are hinged together and linked by multiple sets of side links of the connecting rod mechanism, and the clamping joint at the lower end of the center shaft is pressed and docked with the axial position of the machine wheel shaft; the inner side of the lower end of the claw angle grasps the accessory, so that the center shaft and the nut sleeve rotate in the opposite direction, and the claw angle drives the accessory to move in the opposite direction relative to the machine wheel shaft, thereby achieving the purpose of disassembly.

Description

Technical Field

[0001] The invention relates to aircraft ground support equipment, which is suitable for disassembly, maintenance and support of aircraft wheel accessories, and in particular to an aircraft wheel accessory disassembly device and a disassembly method. Background Art

[0002] Wheels are a crucial component of an aircraft's landing system, bearing the impact loads of hundreds of tons during takeoff and high-speed taxiing, as well as hundreds of tons during landing. A wheel is a complex assembly centered around the axle, surrounded by a variety of wheel accessories, including brakes and tapered roller bearings. These accessories vary significantly in appearance and structure, as well as their installation locations on the axle. To ensure optimal wheel rolling performance at all times, users must periodically disassemble, replace, and maintain these accessories during routine maintenance. Currently, aircraft are equipped with a variety of disassembly tools with similar structures but single functions. Users have expressed concerns about the wide variety of tools, making their storage and management inconvenient, and have suggested comprehensive improvements. Drawing on current disassembly operation models, a device for disassembling aircraft wheel accessories is proposed. This device can quickly and easily meet the disassembly and maintenance needs of multiple wheel accessories, and can also be expanded to include disassembly and maintenance of accessories for civilian equipment, such as those required for wheel maintenance and support in the automotive sector. Summary of the Invention

[0003] In order to meet the maintenance needs of aircraft wheels and overcome the shortcomings of the existing technology, the purpose of this application is to provide an aircraft wheel accessory disassembly device and disassembly method.

[0004] A device for disassembling an aircraft wheel accessory, characterized in that the disassembly device comprises a central shaft and an accessory clamping mechanism, wherein the central shaft is a rigid screw structure, a compression joint is provided at the lower end of the central shaft, and a first handle is provided at the upper end of the central shaft, and the accessory clamping mechanism comprises a nut sleeve, a lug nut, a lug ring, a plurality of claw angles and a plurality of connecting rod assemblies, the nut sleeve is an internal and external double-sided threaded structure, the internal thread of which is connected to the external thread of the rigid screw, and the external thread of which is connected to the internal thread of the lug nut, the outer side of the lug nut is provided with a plurality of radial lugs, and the lug nut is screwed to the screw through the internal thread. On the outside of the female sleeve, the support earring is an annular structure. The support earring is located below the nut sleeve and is movably connected to the screw of the central axis. A plurality of radial ear pieces are also provided on the outside of the support earring. Each radial ear piece is hinged to the top of a claw angle. The connecting rod assembly contains an upper connecting rod and two side connecting rods. The two side connecting rods are respectively hinged at the two sides of the lower end of the upper connecting rod. The upper end of each connecting rod assembly is hinged to a radial ear piece of the support ear nut. The two side connecting rods of each connecting rod assembly are respectively hinged to the middle parts of two adjacent claw angles. The middle parts of all claw angles are hinged together and linked through multiple sets of side connecting rods of the connecting rod mechanism.

[0005] The aircraft wheel attachment removal device is characterized in that a transverse rod passing through the claw angle body is provided in the middle of the claw angle, and the two side connecting rods of each connecting rod assembly are respectively hinged on the transverse rod of the adjacent claw angle.

[0006] The aircraft wheel accessory disassembly device is characterized in that the lug nut is provided with three groups of radial double ear pieces, and the outer side of the lug ring is also provided with three groups of radial double ear pieces. Three groups of connecting rod assemblies hinge the lug nut and the middle parts of the three claw angles together in a linked manner, and the upper ends of the three claw angles are respectively hinged to the three groups of radial double ear pieces of the lug ring.

[0007] A method for disassembling an aircraft wheel accessory comprises a wheel axle and an accessory connected to the wheel axle, and is characterized by comprising the following contents: 1) using the above-mentioned aircraft wheel accessory disassembly device; 2) pressing and docking the compression joint at the lower end of the central shaft with the axial center position of the wheel axle; 3) rotating the second handle to adjust the position of the lug nut on the nut sleeve, so that the lug nut moves upward along the nut sleeve, and the connecting rod assembly drives the claw angle to open; 4) rotating the first handle to adjust the height of the nut sleeve on the central shaft, and the nut sleeve drives the lug nut and the lug ring to achieve the coordination of the height of the claw angle of the accessory clamping mechanism and the position of the accessory; 5) rotating the second handle to adjust the position of the lug nut on the nut sleeve, so that the lug nut moves downward along the nut sleeve, and the connecting rod assembly pushes the claw angle to close, so that the inner side of the lower end of the claw angle grasps the accessory; 6) through the reverse force of the first handle and the second handle, the central shaft and the nut sleeve are rotated in the opposite direction, and the claw angle drives the accessory to move in the opposite direction relative to the wheel axle, thereby achieving the purpose of disassembly.

[0008] The beneficial effects of the present application are as follows: 1) The aircraft wheel accessory disassembly device of the present application is a double-threaded structure coordinated with a connecting rod mechanism to realize infinite adjustment of the movable connection and clamping posture, and can quickly realize the up and down movement adjustment or opening and closing adjustment of the three sets of claw angles, meeting the maintenance and disassembly requirements of wheel accessories of various specifications. It has the advantages of simple structure and easy operation. 2) By changing the claw angles and nut sleeves with different structural parameters on the existing basis, it can meet the disassembly requirements of wheel accessories of a full range of specifications within the diameter range, and can also be promoted for use in the automotive field for wheel maintenance and protection needs. It has the advantage of high promotion value.

[0009] The present application is described in further detail below with reference to the accompanying drawings of the embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] Figure 1 This is a structural diagram of an aircraft wheel accessory removal device.

[0011] Figure 2 It is a schematic diagram of the nut sleeve structure.

[0012] Figure 3 Schematic diagram of the lug nut structure.

[0013] Figure 4 Schematic diagram of the earring structure.

[0014] Figure 5 Schematic diagram of the claw angle structure.

[0015] Figure 6 This is a schematic diagram of the disassembly method for aircraft wheel accessories.

[0016] Explanation of numbers in the figure: 1 center shaft, 2 nut sleeve, 3 ear nut, 4 earring, 5 connecting rod assembly, 6 claw angle, 7 clamping joint, 8 first handle, 9 second handle, 10 upper connecting rod, 11 side connecting rod, 12 right angle, 13 transverse rod, 14 machine wheel axle, 15 accessories. DETAILED DESCRIPTION

[0017] Referring to the accompanying drawings, the aircraft wheel attachment removal device of the present application is as follows: Figure 1 As shown, the disassembly device includes a central shaft 1 and an accessory clamping mechanism. The central shaft 1 is a rigid screw structure. A compression joint 7 is provided at the lower end of the rigid screw. A first handle 8 is provided at the upper end of the central shaft 1. The accessory clamping mechanism includes a nut sleeve 2, a lug nut 3, a lug ring 4, three claw angles 6 and three connecting rod assemblies 5. The nut sleeve 2 is as shown in FIG. Figure 2 As shown, a second handle 9 is provided at the upper end of the nut sleeve 2. The nut sleeve 2 is a double-sided threaded structure, wherein the internal thread is connected to the external thread of the rigid screw of the central axis 1, and the external thread is connected to the internal thread of the lug nut 3. The lug nut 3 is as shown in FIG. Figure 3 As shown, the outer side of the lug nut 3 is provided with three pairs of radial double-ear structures, and the lug nut 3 is screwed to the outer side of the nut sleeve 2 through the internal thread. Figure 4 As shown, the support lug 4 is an annular structure located below the nut sleeve 2 and movably connected to the screw of the central shaft 1. The outer side of the support lug 4 is also provided with three pairs of radial double-ear structures, each pair of radial ears being hinged to the top of a claw angle 6. The connecting rod assembly 5 includes an upper connecting rod 10 and two side connecting rods 11, which are hinged to the sides of the lower end of the upper connecting rod 10. The upper end of each connecting rod assembly 5 is hinged to the pair of radial double-ears of the support lug nut 3. The two side connecting rods 11 of each connecting rod assembly 5 are respectively hinged to the middle portions of two adjacent claw angles 6. In practice, a transverse rod 13 is provided in the middle portion of the claw angle 6, passing through the claw angle body. The two side connecting rods 11 of each connecting rod assembly are spherically hinged to the transverse rod 13 of the adjacent claw angle 6. The three sets of side connecting rods 11 of the connecting rod mechanism 5 hinge the middle portions of all claw angles 6 together and in a coordinated manner.

[0018] In the embodiment, the claw angle 6 is structured as follows Figure 5 As shown, the inner side of the lower end of the claw angle 6 is a right-angle 12 structure, which is convenient for limiting and clamping the accessories.

[0019] When using the above-mentioned aircraft wheel accessory disassembly device to disassemble an aircraft wheel accessory, the compression joint 7 at the lower end of the central shaft 1 is pressed and connected to the axial position of the wheel shaft 14; the second handle 9 is rotated to adjust the position of the lug nut 3 on the nut sleeve 2, so that the lug nut 3 moves upward along the nut sleeve 2, and the connecting rod assembly 5 drives the claw angle 6 to open; the first handle 8 is rotated to adjust the height of the nut sleeve 2 on the central shaft 1, and the nut sleeve 2 drives the lug nut 3 and the lug ring 4 to adjust the height of the claw angle 6 of the accessory clamping mechanism to coordinate with the position of the accessory; the second handle 9 is rotated to adjust the position of the lug nut 3 on the nut sleeve 2 again, so that the lug nut 3 moves downward along the nut sleeve 2, and the connecting rod assembly 5 pushes the claw angle 6 to close, so that the right angle 12 on the inner side of the lower end of the claw angle 6 grabs the accessory 15; by applying opposite forces of the first handle 8 and the second handle 9, the central shaft 1 and the nut sleeve 2 are rotated in the opposite direction, and the claw angle 6 drives the accessory 15 to move in the opposite direction relative to the wheel shaft 14, thereby achieving the purpose of disassembly.

Claims

1. An aircraft wheel accessory removal device, characterized in that: The disassembly device contains a central shaft and an accessory clamping mechanism, the central shaft is a rigid screw structure, a compression joint is provided at the lower end of the central shaft, and a first handle is provided at the upper end of the central shaft, the accessory clamping mechanism contains a nut sleeve, a lug nut, a lug ring, multiple claw angles and multiple connecting rod assemblies, the nut sleeve is an internal and external double-sided threaded structure, its internal thread is connected to the external thread of the rigid screw, and its external thread is connected to the internal thread of the lug nut, the outer side of the lug nut is provided with multiple radial ear pieces, the lug nut is screwed to the outer side of the nut sleeve through the internal thread, the lug nut is provided with three groups of radial double ear pieces, and the outer side of the lug ring is also provided with three groups of radial double ear pieces, and there are three groups of connecting rod assemblies that hinge the lug nut and the middle part of the three claw angles together, and the upper ends of the three claw angles are respectively connected to the three ends of the lug ring. The radial double ear pieces are hinged in correspondence. The support earring is an annular structure. The support earring is located below the nut sleeve and is movably sleeved on the screw of the central axis. A second handle is provided at the upper end of the nut sleeve. A plurality of radial ear pieces are also provided on the outside of the support earring. Each radial ear piece is hinged to the top of a claw angle. The connecting rod assembly contains an upper connecting rod and two side connecting rods. The two side connecting rods are respectively hinged at the two sides of the lower end of the upper connecting rod. The upper end of each connecting rod assembly is hinged to a radial ear piece of the support ear nut. The two side connecting rods of each connecting rod assembly are respectively hinged to the middle parts of two adjacent claw angles. There is a transverse rod passing through the claw angle body in the middle of the claw angle. The two side connecting rods of each connecting rod assembly are respectively hinged on the transverse rods of the adjacent claw angles. The middle parts of all claw angles are hinged together and linked through multiple groups of side connecting rods of the connecting rod mechanism.

2. The aircraft wheel attachment removal device according to claim 1, wherein: The inner side of the lower end of the claw angle is a right-angle structure.

3. A method for disassembling an aircraft wheel accessory, comprising a wheel axle and accessories connected to the wheel axle, characterized in that The invention comprises the following contents: 1) using the aircraft wheel accessory disassembly device as described in any one of claims 1-2; 2) pressing and docking the compression joint at the lower end of the center shaft with the axial position of the wheel shaft; 3) rotating the second handle to adjust the position of the lug nut on the nut sleeve, so that the lug nut moves up along the nut sleeve, and the connecting rod assembly drives the claw angle to open; 4) rotating the first handle to adjust the height of the nut sleeve on the center shaft, and driving the lug nut and the lug ring through the nut sleeve to adjust the height of the claw angle of the accessory clamping mechanism and coordinate with the position of the accessory; 5) rotating the second handle to adjust the position of the lug nut on the nut sleeve, so that the lug nut moves downward along the nut sleeve, and the connecting rod assembly pushes the claw angle to close, so that the inner side of the lower end of the claw angle grasps the accessory; 6) through the reverse force of the first handle and the second handle, the center shaft and the nut sleeve are rotated in the opposite direction, and the claw angle drives the accessory to move in the opposite direction relative to the wheel shaft, thereby achieving the purpose of disassembly.

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