Auxiliary device for disassembly and assembly of undercarriage

By designing an auxiliary device for landing gear disassembly and assembly, using components such as I-shaped support seats, wheel casters, support rods and tightening belts, the problems of difficulty in moving, complex operation and safety hazards during landing gear disassembly and assembly are solved, and a more efficient, safe and labor-saving operation process is achieved.

CN119659973APending Publication Date: 2025-03-21GUANGZHOU AIRCRAFT MAINTENANCE ENG
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Patent Information

Application Number
CN202411849570.8
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2024-12-16
Publication Date
2025-03-21

AI Technical Summary

Technical Problem

The prior art has many inconveniences in the disassembly and assembly of landing gears, including difficulty in movement caused by ground friction, complex operation and inefficiency, and lack of special fixing and support tools, which leads to the landing gear being easily tilted and offset, posed safety hazards and extended working time.

Method used

A landing gear disassembly and assembly auxiliary device is designed, including I-shaped support seats, lockable wheel casters, support rods, guide rails, sliders, axle apex seats and tightening belts. Through the cooperation of these components, stable load bearing and flexible transfer of the landing gear can be achieved.

Benefits of technology

This device significantly improves the safety, efficiency and labor-saving of landing gear disassembly and assembly operations, reduces dependence on CTI, shortens the operation cycle, and reduces the cost of manpower and material consumption.

✦ Generated by Eureka AI based on patent content.

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Abstract

The invention relates to an undercarriage disassembly and assembly auxiliary device which comprises an I-shaped supporting base, lockable casters are installed below the two ends of two transverse frames of the I-shaped supporting base respectively, supporting rods are vertically installed above the two ends of the transverse frames respectively, a guide rail is arranged on a bracket between the two transverse frames, and at least two sliding blocks are arranged on the guide rail. The sliding block is provided with a wheel axle vertex seat matched with two wheel axle vertexes of the undercarriage, when the undercarriage is placed on the auxiliary device, the undercarriage is supported on the two wheel axle vertex seats of the bracket through the two wheel axle vertexes of the undercarriage so as to be suspended, wheels of the undercarriage are distributed on the two sides of the bracket, and the whole undercarriage is located between the two transverse frames; the auxiliary device further comprises a fixing sleeve and a tightening belt, wherein the fixing sleeve is used for being arranged on the undercarriage inner cylinder in a sleeving mode, and the tightening belt is connected with the supporting rod and the fixing sleeve so as to tighten the undercarriage inner cylinder from different directions to keep the position of the undercarriage inner cylinder stable. By means of the auxiliary device, the landing gear can be disassembled and assembled more safely, efficiently and effortlessly.
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Description

Technical Field

[0001] The invention relates to the field of aircraft maintenance, and in particular to a landing gear disassembly and assembly auxiliary device. Background Art

[0002] Aircraft landing gear is a key life-span component, and regular inspection and replacement are essential to ensure flight safety. However, the current landing gear replacement process faces many challenges and inconveniences.

[0003] The landing gear is a complete disassembly component. After being removed from the aircraft body, it is placed directly on the ground, which not only increases the difficulty of disassembling delicate components such as wheels and brakes, but also makes it extremely inconvenient to move due to ground friction. In conventional operations, in order to push the landing gear out from under the aircraft wing, it is often necessary to lay grease sliders under the landing gear wheels to reduce friction, but this is not only complicated to operate, but also difficult to accurately control the direction, and inefficient.

[0004] What is particularly tricky is that when the wheels and brake system of the landing gear need to be further removed, the traditional method requires the use of CTI (crane and transport equipment) for lifting operations, so that the heavy landing gear is suspended in the air for subsequent disassembly. During this process, due to the lack of special fixing and supporting tools, the landing gear is very likely to tilt and deflect, which not only threatens the safety of the operators, but also greatly prolongs the operation time and increases the labor intensity.

[0005] In terms of the specific operation process, the current practice usually includes the following cumbersome steps:

[0006] First, the side struts, front and rear pivot pins, hydraulic lines and connecting wires connected to the landing gear must be carefully disconnected to ensure that the landing gear can be safely separated from the aircraft.

[0007] Then, the CTI was used to slowly lift the landing gear off the aircraft and place it on the ground;

[0008] Next, the grease slide was laid and the landing gear was pushed to the appropriate position by manpower, and then the CTI was used again to lift the landing gear to disassemble the wheels and brake system;

[0009] Finally, the disassembled landing gear is placed on a special bracket for storage.

[0010] As can be seen from the above, the entire disassembly process of the landing gear involves multiple links, including laying grease, manually pushing the slider, and multiple CTI lifting. It is not only time-consuming and labor-intensive, but also has safety hazards that cannot be ignored.

[0011] Take the Boeing 767 as an example. According to the traditional practice, the disassembly and assembly of its landing gear and the replacement of wheels, brake system and other parts take up to 192 working hours, that is, 8 days x 24 hours. This long operation cycle not only affects the normal maintenance and operation plan of the aircraft, but also has an adverse impact on the economic benefits and service quality of the airline. Therefore, developing a safe, efficient and labor-saving landing gear disassembly and assembly operation plan has become an important issue that needs to be solved in the current aviation maintenance field. Summary of the invention

[0012] The present invention aims to provide a landing gear disassembly and assembly auxiliary device, by which the landing gear disassembly and assembly operation can be made safer, more efficient and labor-saving.

[0013] The present invention achieves its invention purpose through the following technical solutions: an auxiliary device for disassembling and assembling a landing gear, comprising an I-shaped support seat, wherein two ends of two horizontal frames are respectively provided with lockable casters below, and support rods are respectively vertically provided above, a guide rail is provided on a bracket between the two horizontal frames, at least two sliders are provided on the guide rail, and a wheel axle vertex seat for cooperating with two wheel axle vertices of the landing gear is provided on the slider, when the landing gear is placed on the auxiliary device, the two wheel axle vertices of the landing gear are supported on the two wheel axle vertex seats of the bracket and are suspended, and the wheels are distributed on both sides of the bracket and are located as a whole between the two horizontal frames;

[0014] The auxiliary device also includes a fixing sleeve for sleeved on the landing gear inner tube, and a tightening belt connecting the support rod and the fixing sleeve so as to tighten the landing gear inner tube from different directions to keep its position stable.

[0015] The support rod is hinged to the cross frame through a hinge shaft and can be folded on the cross frame so as to be folded when placing the landing gear on the auxiliary device and unfolded after the landing gear is placed, which facilitates the placement operation of the landing gear.

[0016] The hinge of the support rod is formed with two sets of opposite openings, one for inserting the hinge shaft, and the other for inserting a pin parallel to the hinge shaft to fix the support rod after the support rod is unfolded, so as to enhance the stability of the support rod in the unfolded state.

[0017] A lifting ring is fixed on the upper end of the support rod, and the lifting ring is used to facilitate the connection between the tightening belt and the support rod.

[0018] The support seat is also provided with a towing point for conveniently towing the auxiliary device.

[0019] As a preferred solution, four sliders are arranged on the guide rail, wherein two outer sliders are provided with auxiliary fixing rods for cooperating with the front and rear towing points of the landing gear to achieve locking.

[0020] The fixing sleeve is a clamp with a plurality of holes distributed circumferentially, and the arrangement of the holes facilitates the connection of the tightening belt.

[0021] The slider is provided with a locking screw for locking the slider on the slide rail.

[0022] The auxiliary fixing rod is a screw having a threaded upper portion and two nuts mounted thereon. When the landing gear is placed on the auxiliary device, the screw is inserted into a hole on the landing gear towing point, and the lower nut is supported under the towing point and cooperates with the upper nut to lock the towing point.

[0023] Except for some models without towing points, for most models, the auxiliary fixing rod can be used to strengthen the fixing of the landing gear on the auxiliary device. However, the height of the towing points of each model is not the same. The towing points are locked by two movable nuts. This design has good versatility.

[0024] Beneficial effects:

[0025] 1) After the landing gear is disconnected from the main body of the aircraft, the landing gear is placed on the auxiliary device of the present invention through CTI. The auxiliary device supports the landing gear by the cooperation between the axle apex seat and the landing gear axle apex, and tightens the landing gear from different directions through the cooperation between the support rod, the fixing sleeve, the tightening belt and the landing gear inner tube, so as to achieve stable load-bearing and flexible transfer of the landing gear. In addition, the disassembly and assembly of the landing gear wheels and the brake system can be directly performed on the auxiliary device of the present invention, which reduces the dependence on CTI, is safer, more efficient, and also more labor-saving. In addition, after directly pushing the auxiliary device to the appropriate position and locking the wheel casters, the stable storage of the landing gear can be achieved. The present invention completely revolutionizes the operation process of disassembly, transfer and storage of the landing gear in traditional operations, and overcomes a major technical problem. The use of the auxiliary device of the present invention can not only significantly reduce the dual costs of human resources and material consumption, but also greatly shorten the operation cycle. For example, the total time consumed by using the auxiliary device of the present invention to perform the displacement of the landing gear and the disassembly and assembly of the wheels and brake system is only 64 working hours, that is, 4 people × 16 hours. Compared with the traditional method, the working hours are reduced by more than half.

[0026] 2) The auxiliary device of the present invention also has good versatility: the structures of the axle vertices of the landing gears of various models are basically the same, and the distance between the two axle vertices may be slightly different. The auxiliary device of the present invention supports the landing gear by cooperating between the two axle vertices seats with adjustable distance and the axle vertices of the landing gear. Therefore, it has good versatility and is basically applicable to the landing gears of all current models. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is a structural schematic diagram of an auxiliary device of a preferred embodiment of the present invention;

[0028] Figure 2 for Figure 1 Reference diagram of the auxiliary device in use;

[0029] Figure 3 for Figure 1 An enlarged view of the supporting structure of the auxiliary device to the landing gear. DETAILED DESCRIPTION

[0030] like Figure 1-3 As shown, the auxiliary device of this embodiment includes an I-shaped support seat 1, and lockable casters are respectively installed below the two ends of the two cross frames, and support rods 6 are respectively installed vertically above, and a lifting ring 4 is also fixed to the upper end of the support rod 6. The lifting ring 4 is used to facilitate the connection between the tightening belt 7 and the support rod 6 mentioned later. The support rod 6 is hinged to the cross frame through a hinge shaft 61 and can be folded on the cross frame so that it can be folded during the placement of the landing gear F, and then unfolded after the landing gear F is placed, thereby facilitating the placement operation of the landing gear F. In fact, two sets of opposite openings are formed at the hinge of the support rod 6, one for inserting the hinge shaft 61, and the other for inserting a pin 62 parallel to the hinge shaft 61 after the support rod 6 is unfolded to achieve the fixation of the support rod 6, so as to enhance the stability of the support rod 6 in the unfolded state.

[0031] A guide rail 11 is provided at each end of the bracket between the two cross frames, and two sliders 14 are provided at the front and rear of each guide rail 11. The two outer sliders 14 of the four sliders 14 are provided with auxiliary fixing rods 3 for cooperating with the towing points 18 at the front and rear of the landing gear F to achieve locking. In this embodiment, the auxiliary fixing rod 3 is a screw rod 12 with a thread formed on the upper part and two nuts 13 and 10 are mounted thereon. Figure 3 As shown, when the landing gear F is placed on the auxiliary device, the screw rod 12 is inserted into the hole on the towing point 18 of the landing gear F, and the nut 13 at the bottom is supported under the towing point 18, and cooperates with the nut 10 at the top to lock the towing point 18 of the landing gear F. A nylon protective sleeve is also tightly attached to the screw rod 12, and its function is to prevent it from being scratched when it contacts the hole on the towing point 18.

[0032] Except for some aircraft types that are not designed with a towing point 18, for most aircraft types, the fixing of the landing gear F on the auxiliary device can be strengthened by the auxiliary fixing rod 3. However, the height of the towing point 18 of each aircraft type is not the same, and the locking of the towing point 18 is achieved by two movable nuts 13, 10, which has better versatility.

[0033] The two inner slide blocks 14 are provided with axle apex seats 2 for cooperating with the two axle apex 19 of the landing gear F. Figure 2 , 3As shown, when the landing gear F is placed on the auxiliary device, it is suspended in the air by supporting the two axle vertices 19 on the two axle vertices seats 2 of the bracket, and the wheels of the landing gear F are distributed on both sides of the bracket and are located between the two cross frames as a whole. The end of the axle vertices 19 of the landing gear F itself is a semicircular protrusion, and the corresponding axle vertices seat 2 forms a semicircular depression to accommodate it. After the two are connected, a good support relationship is formed.

[0034] The structures of the axle vertices 19 of the landing gears F of various models are basically the same, and the distance between the two axle vertices 19 may be slightly different. In this embodiment, the auxiliary device supports the landing gear F by cooperating between the two axle vertices seats 2 with adjustable distance and the axle vertices 19 of the landing gear F, so that the auxiliary device of this embodiment has good versatility and is basically applicable to all current models.

[0035] like Figure 1 As shown, a towing bar 5 for facilitating towing an auxiliary device is also provided on the cross bar.

[0036] like Figure 3 As shown, locking screws 15 and 16 are provided on the slider 14 . The locking screw 15 is used to lock the slider 14 on the bottom surface of the slide rail 11 , and the locking screw 16 is used to lock the slider 14 on the side surface of the slide rail 11 .

[0037] like Figure 2 As shown, the auxiliary device also includes a fixing sleeve 8 for sleeved on the inner tube 9 of the landing gear F, and a tightening belt 7 connecting the support rod 6 (the lifting ring 4 at the end of the support rod 6 is not shown in the figure) and the fixing sleeve 8 so as to tighten the inner tube 9 of the landing gear F from different directions to keep its position stable. In this embodiment, the fixing sleeve 8 is a clamp with a plurality of holes distributed circumferentially, and the arrangement of the holes makes it convenient for users to connect with the tightening belt 7 made of nylon.

[0038] The process of disassembling and assembling the landing gear F using the auxiliary device of this embodiment is as follows:

[0039] 1) Remove the landing gear F from the aircraft, lift the landing gear F to a suitable height by CTI, manually move the auxiliary device to the bottom of the landing gear F, adjust the distance between the two wheel axle head seats 2 and the two auxiliary fixing rods 3 on the auxiliary device slide rail 11, so that they are aligned with the wheel axle apex 19 and the front and rear towing points 18 of the landing gear F respectively, and slowly lower the landing gear F to support it on the auxiliary device.

[0040] 2) Lock the towing points 18 at the front and rear of the landing gear F through nuts 13 and 10, and tighten the locking screws 15 and 16 on the slider 14.

[0041] 3) Expand the four support rods 6 arranged at both ends of the I-shaped support base 1.

[0042] 4) The fixing sleeve 8 is put on the inner tube 9 of the landing gear F, and the tightening belts 7 are passed through the circumferential holes of the fixing sleeve 8 and the lifting rings 4 of the support rod 6 and then tightened so that the four tightening belts 7 are evenly stressed.

[0043] 5) Manually push the auxiliary device out from under the aircraft wing, then lock the casters of the auxiliary device. After the auxiliary device is fixed, normal disassembly and assembly of the landing gear F wheels and brake system can be carried out.

[0044] 6) Push the auxiliary device to a suitable position, lock its casters, and place the landing gear F directly on the auxiliary device for storage, which can greatly improve the flexibility of storage and transfer of the landing gear F.

[0045] The auxiliary device of the present invention supports the landing gear by cooperating with the axle vertex seat and the landing gear axle vertex, and tightens the landing gear from different directions by cooperating with the support rod, the fixing sleeve, the tightening belt and the landing gear inner tube, so as to realize stable load-bearing and flexible transfer of the landing gear. The auxiliary device of the present invention is used to support the disassembled landing gear, which not only supports 360-degree rotation and displacement of the landing gear, but also has significantly better load-bearing capacity and stability than the current CTI suspension solution. The landing gear wheels and brake system can be disassembled and assembled directly on it, which can ensure the safety and efficiency of the operation process.

Claims

1. A landing gear disassembly and assembly auxiliary device, characterized in that: It comprises an I-shaped support seat, wherein two ends of the two horizontal frames are respectively provided with lockable casters below, and support rods are respectively vertically provided above, a guide rail is provided on the bracket between the two horizontal frames, and at least two sliders are provided on the guide rail, and a wheel axle vertex seat for cooperating with the two wheel axle vertices of the landing gear is provided on the slider, and when the landing gear is placed on the auxiliary device, the two wheel axle vertices are supported on the two wheel axle vertex seats of the bracket and suspended in the air, and the wheels are distributed on both sides of the bracket, and the whole is located between the two horizontal frames; The auxiliary device also includes a fixing sleeve for sleeved on the landing gear inner tube, and a tightening belt connecting the support rod and the fixing sleeve so as to tighten the landing gear inner tube from different directions to keep its position stable.

2. The auxiliary device according to claim 1, characterized in that The support rod is hinged to the cross frame through a hinge shaft and can be folded on the cross frame.

3. The auxiliary device according to claim 2, characterized in that The hinge of the support rod is formed with two groups of opposite openings, one of which is used to penetrate the hinge shaft, and the other is used to insert a pin parallel to the hinge shaft to fix the support rod after the support rod is unfolded.

4. The auxiliary device according to claim 1, characterized in that A lifting ring is fixed on the upper end of the supporting rod.

5. The auxiliary device according to claim 1, characterized in that The support seat is also provided with a towing point for conveniently towing the auxiliary device.

6. The auxiliary device according to claim 1, characterized in that The fixing sleeve is a clamp with a plurality of holes distributed circumferentially.

7. The auxiliary device according to claim 1, characterized in that The slider is provided with a locking screw for locking the slider on the slide rail.

8. The auxiliary device according to any one of claims 1 to 7, characterized in that: Four sliders are arranged on the guide rail, wherein two outer sliders are provided with auxiliary fixing rods for cooperating with the front and rear towing points of the landing gear to achieve locking.

9. The auxiliary device according to claim 8, characterized in that The auxiliary fixing rod is a screw having a threaded upper portion and two nuts mounted thereon. When the landing gear is placed on the auxiliary device, the screw is inserted into a hole on the landing gear towing point, and the lower nut is supported under the towing point and cooperates with the upper nut to lock the towing point.