Aircraft landing gear outer tube dismounting and mounting auxiliary device

Abstract

The utility model discloses an aircraft landing gear outer tube dismounting auxiliary device, it includes two centering sleeve, bearing rod, gyro wheel and locking nut, two centering sleeve are used for wearing in the mounting hole of the ear of outer tube upper end two sides respectively, and one end of centering sleeve is equipped with the flange for abutting on the outer end surface of mounting hole, and the perforation is equipped on two centering sleeve respectively, and bearing rod passes through the perforation of two centering sleeve, and the head of bearing rod abuts on the outer end of the perforation of one centering sleeve, and the tail of bearing rod is equipped with outer thread, and locking nut is connected in the tail of bearing rod with thread, and gyro wheel is established on bearing rod, and gyro wheel is used as the bearing point of pull rope in the maintenance process. The utility model can better guarantee the security and stability in the process of outer tube dismounting, reduce the risk of damaging outer tube and shortening mechanism.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft landing gear maintenance technology, specifically relating to an auxiliary device for disassembling and assembling the outer cylinder of an aircraft landing gear. Background Technology

[0002] The outer cylinder of the aircraft landing gear is the main load-bearing component of the landing gear. The outer cylinder 9 is fitted onto the landing gear shock absorber strut 10, and its upper end is provided with lugs 14 and other structures for connection with the aircraft. Specifically, there are three lugs 14 on the upper end of the outer cylinder 9, and each lug 14 has a mounting hole 15. One lug 14 is located on one side of the upper end of the outer cylinder 9, and the other two lugs 14 are located on the other side of the upper end of the outer cylinder 9. There is a through hole 13 between the lugs 14 on both sides. A shortening mechanism 11 is connected to the upper end of the shock absorber strut 10, and the position of the shortening mechanism 11 corresponds to the position of the through hole 13.

[0003] During routine landing gear maintenance, the outer cylinder 14 is frequently disassembled and reassembled. Before disassembly, the retaining pin of the internal shortening mechanism 11 needs to be removed, which will leave the shortening mechanism 11 in a free state. At this point... Figure 4 As shown. In this case, the shortening mechanism 11 needs to be pulled up to keep it vertical and avoid contact with the inside of the outer cylinder 9 before the outer cylinder 9 can be lifted upwards to separate it from the shock absorber support 10. During installation, the shortening mechanism 11 also needs to be pulled up to keep it vertical before the outer cylinder 9 can be fitted onto the shock absorber support 10 from top to bottom. The lifting and lowering of the outer cylinder 9 requires a crane. During maintenance, the crane hook 17 will be connected to the lugs 14 on both sides of the upper end of the outer cylinder 9 via the sling 16.

[0004] In current maintenance practices, the industry typically uses a pull rope 12, with one end tied to the upper end of the shortening mechanism 11. The rope 12 is then looped around the crane hook 17, which serves as the load-bearing point. Workers tighten the other end of the rope 12, and in conjunction with the raising and lowering of the outer cylinder 9, the rope 12 is lengthened or shortened to keep the shortening mechanism 11 vertical. However, because the hook 17 is connected to both the sling 16 and the pull rope 12, the sling 16 is prone to tangling and jamming with the rope 12 during operation. This can easily cause the shortening mechanism 11 to shift, resulting in damage to both the outer cylinder 9 and the shortening mechanism 11. The outer cylinder 9 of the aircraft landing gear is an expensive part, and repairing its internal components is extremely difficult; damage would significantly increase aircraft maintenance costs. Therefore, a specialized tool is urgently needed to ensure low-risk disassembly and assembly of the landing gear outer cylinder. Utility Model Content

[0005] The purpose of this invention is to provide an auxiliary device for disassembling and assembling the outer cylinder of an aircraft landing gear, which can better ensure the safety and stability of the disassembly and assembly process, and reduce the risk of damaging the outer cylinder and shortening the mechanism.

[0006] The objective of this utility model is achieved through the following technical solution:

[0007] An auxiliary device for disassembling and assembling an aircraft landing gear outer cylinder is characterized by comprising two centering sleeves, a support rod, a roller, and a locking nut. The two centering sleeves are respectively used to pass through the mounting holes of the lugs on both sides of the upper end of the outer cylinder. One end of the centering sleeve is provided with a flange for abutting against the outer end face of the mounting hole. The two centering sleeves are respectively provided with through holes. The support rod passes through the through holes of the two centering sleeves. The head of the support rod abuts against the outer end of the through hole of one centering sleeve. The tail of the support rod is provided with an external thread. The locking nut is threadedly connected to the tail of the support rod. The roller is provided on the support rod and is used as a load-bearing point for the pull rope during maintenance.

[0008] A further technical solution of this utility model is: one side of one of the centering sleeves is a plane, and when the centering sleeve with the plane is inserted into the mounting hole of the lug, a gap is formed between the plane and the inner wall of the mounting hole for the sling to pass through.

[0009] A further technical solution of this utility model is: one of the centering sleeves is cylindrical.

[0010] A further technical solution of this utility model is: a sleeve hole is provided in the middle of the roller, and the roller is sleeved on the load-bearing rod through the sleeve hole.

[0011] A further technical solution of this utility model is: the roller is provided with a groove for the pull rope to pass around.

[0012] Compared with the prior art, the present invention has the following beneficial effects:

[0013] When disassembling and assembling the outer casing of a wide-body civil aircraft, the disassembly and assembly auxiliary device of this utility model uses centering sleeves inserted into the mounting holes of the lugs at the upper end of the outer casing. The two centering sleeves are then locked together using a support rod and a locking nut, achieving a mating connection with the landing gear outer casing lugs. This securely mounts the device to the upper end of the outer casing. A pull rope is then used to connect the shortening mechanism. The pull rope passes over a roller, which serves as the load-bearing point for the rope. This allows workers to lengthen or shorten the rope according to the raising and lowering of the outer casing during disassembly, thus keeping the shortening mechanism in a vertical position. It is evident that during the disassembly and assembly process using this utility model, the pull rope is separate from the sling connected to the crane hook, preventing contact between the pull rope and the sling. This ensures that the shortening mechanism does not shift during the disassembly and assembly of the outer casing, significantly reducing the risk of damage to the outer casing and the shortening mechanism. Attached Figure Description

[0014] Figure 1 This is a three-dimensional structural diagram of the disassembly and assembly auxiliary device according to an embodiment of the present utility model;

[0015] Figure 2This is a front view schematic diagram of the disassembly and assembly auxiliary device according to an embodiment of the present utility model;

[0016] Figure 3 This is a schematic diagram of the disassembly and assembly auxiliary device of this utility model when it is installed on the upper end of the outer cylinder to disassemble the outer cylinder;

[0017] Figure 4 This is a schematic diagram of the shortening mechanism's retaining pin being removed during the disassembly process described in the background art.

[0018] Meaning of the labels in the attached diagram:

[0019] 1-Centering sleeve; 2-Roller; 3-Bearing rod; 4-Flange; 5-Head; 6-Slide groove; 7-Locking nut; 8-Flat surface; 9-Outer cylinder; 10-Shock absorber support; 11-Shortening mechanism; 12-Pull rope; 13-Through hole; 14-Ear; 15-Mounting hole; 16-Helping strap; 17-Hook; 18-Gap. Detailed Implementation

[0020] In the description of this utility model, it should be understood that the directional descriptions, such as up, down, front, back, left, right, etc., indicate the directional or positional relationship based on the directional or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.

[0021] In the description of this utility model, "several" means one or more, "multiple" means two or more, "greater than," "less than," and "exceeding" are understood to exclude the stated number, while "above," "below," and "within" are understood to include the stated number. If "first" or "second" is used in the description, it is only for the purpose of distinguishing technical features and should not be construed as indicating or implying relative importance, or implicitly indicating the number of indicated technical features, or implicitly indicating the order of the indicated technical features.

[0022] In the description of this utility model, unless otherwise explicitly defined, terms such as "setting," "installation," and "connection" should be interpreted broadly, and those skilled in the art can reasonably determine the specific meaning of the above terms in this utility model in conjunction with the specific content of the technical solution.

[0023] The present invention will be further described below with reference to embodiments.

[0024] Example:

[0025] like Figure 1 and Figure 2 The image shows the aircraft landing gear outer cylinder disassembly and assembly auxiliary device of this embodiment, which includes two centering sleeves 1, a load-bearing rod 3, a roller 2 and a locking nut 7.

[0026] Two centering sleeves 1 are respectively used to pass through the mounting holes 15 of the lugs 14 on both sides of the upper end of the outer cylinder 9. In this embodiment, one of the centering sleeves 1 is shaped like a cylinder with one-third cut off, so that one side of the centering sleeve 1 forms a plane 8. When the centering sleeve 1 with the plane 8 is passed through the mounting hole 15 of the lug 14, a gap 18 is formed between the plane 8 and the inner wall of the mounting hole 15 for the sling 16 to pass through. The other centering sleeve 2 in this embodiment is cylindrical in shape. When the cylindrical centering sleeve 2 is passed through the mounting hole 15 of the lug 14, it will basically fill the mounting hole 15.

[0027] Both centering sleeves 1 have a flange 4 at one end. When installed on the lug 14 at the upper end of the outer cylinder 9, the flange 4 will abut against the outer end face of the mounting hole 15, thereby restricting the position of the centering sleeve 1.

[0028] Two centering sleeves 1 are each provided with a through hole, through which the support rod 3 passes. One end of the support rod 3 is a hexagonal head 5 with an increased size, and the other end is a tail with external threads. During installation, the head 5 of the support rod 3 abuts against the outer end of the through hole of the centering sleeve 1 with a flat surface 8, and the tail of the support rod 3 protrudes from the through hole of the other centering sleeve 1. A locking nut 7 is connected to the tail of the support rod 3, and the two centering sleeves 1 are tightened and fixed together by tightening the locking nut 7.

[0029] In this embodiment, the roller 2 has a sleeve hole in the middle. During the installation of the support rod 3, the roller 2 will be installed on the support rod 3, and the roller 2 can rotate freely. The roller 2 has a sliding groove 6. During use, the pull rope 12 will pass through the sliding groove 6, and the roller 2 will be used as the load-bearing point for the pull rope 12 during maintenance.

[0030] The process of installing the aircraft landing gear outer cylinder using the aircraft landing gear outer cylinder removal and installation auxiliary device in this embodiment is as follows:

[0031] Step 1: Use external tools to fix the shock absorber support 10 so that it is perpendicular to the ground.

[0032] Step 2: Install the disassembly and assembly auxiliary device of this embodiment onto the outer cylinder 9: Insert the two centering sleeves 1 into the mounting holes 15 of the lugs 14 on both sides of the upper end of the outer cylinder 9, wherein the centering sleeve 1 with the plane 8 is installed on the side of the upper end of the outer cylinder 9 with a single lug 14; then pass the support rod 3 through the through hole of the centering sleeve 1. During this process, place the roller 2 between the two centering sleeves 1 and make the support rod 3 pass through the sleeve hole of the roller 2. Then connect the locking nut 7 to the tail of the support rod 3 and tighten the locking nut 7 to tighten and fix the two centering sleeves 1. The flange 4 of the centering sleeve 1 abuts against the outer end face of the mounting hole 15 of the lug 14.

[0033] Step 3: Wrap a sufficiently long pull rope 12 around the roller 2. One end of the pull rope 12 is inserted through the through hole 13 at the top of the outer cylinder 9, passes through the inside of the outer cylinder 9, and finally comes out from the bottom of the outer cylinder 9. The other end of the pull rope 12 is left outside.

[0034] Step 4: Secure the appropriate sling 16 to the lug 14 of the outer cylinder 9 and connect the sling 16 to the hook 17 of the crane; then lift the outer cylinder 9 with the crane until the outer cylinder 9 is higher than the shock absorber support 10.

[0035] Step 5: Connect the end of the pull rope 12 that passes through the lower end of the outer cylinder 9 to the first section of the shortening mechanism 11 at the upper end of the shock absorber support 10.

[0036] Step 6: Hoist the outer cylinder 9 directly above the shock absorber support 10. The worker pulls the outer end of the rope 12 to straighten the shortening mechanism 11 and make it vertical. Then, slowly lower the outer cylinder 9 onto the shock absorber support 10. While the outer cylinder 9 is falling, the worker must simultaneously pull the rope 12 to keep the shortening mechanism 11 vertical until the outer cylinder 9 falls to the expected installation position.

[0037] Step 7: Untie the pull rope 12, install the fixing pin of the shortening mechanism 11, and remove the disassembly and assembly auxiliary device of this embodiment.

[0038] The disassembly process of the aircraft landing gear outer cylinder auxiliary device in this embodiment is the reverse of the above process: such as Figure 3 As shown, the disassembly and assembly auxiliary device of this embodiment is also installed on the upper end of the outer cylinder 9. The pull rope 12 is passed around the roller 2. One end of the pull rope 12 is connected to the first section of the shortening mechanism 11. The worker pulls the pull rope 12 taut through the other end of the pull rope 12, and then removes the fixing pin of the shortening mechanism 11. Under the tension of the pull rope 12, the shortening mechanism 11 remains in a vertical position. Then, the outer cylinder 9 is slowly and vertically lifted upward by the crane. During this process, the pull rope 12 is kept taut, and the shortening mechanism 11 remains in a vertical position. Finally, the outer cylinder 9 is completely separated from the shock absorber support 10, and the disassembly is completed.

[0039] The above embodiments of this utility model are not intended to limit the scope of protection of this utility model. The implementation of this utility model is not limited thereto. All other modifications, substitutions or alterations made to the above structure of this utility model based on the above content of this utility model and in accordance with the common technical knowledge and conventional means in the field, without departing from the basic technical idea of ​​this utility model, shall fall within the scope of protection of this utility model.

Claims

1. An auxiliary device for disassembling and assembling the outer cylinder of an aircraft landing gear, characterized in that: The device includes two centering sleeves, a support rod, a roller, and a locking nut. The two centering sleeves are respectively used to pass through the mounting holes of the lugs on both sides of the upper end of the outer cylinder. One end of each centering sleeve has a flange for abutting against the outer end face of the mounting hole. Each of the two centering sleeves has a through hole. The support rod passes through the through holes of the two centering sleeves. The head of the support rod abuts against the outer end of the through hole of one centering sleeve. The tail of the support rod has an external thread. The locking nut is threaded to the tail of the support rod. The roller is located on the support rod and is used as a load-bearing point for the pull rope during maintenance.

2. The aircraft landing gear outer cylinder disassembly and assembly auxiliary device according to claim 1, characterized in that: One side of one of the centering sleeves is flat, and when the centering sleeve with the flat surface is inserted into the mounting hole of the lug, a gap is formed between the flat surface and the inner wall of the mounting hole for the sling to pass through.

3. The aircraft landing gear outer cylinder disassembly and assembly auxiliary device according to claim 1, characterized in that: One of the centering sleeves is cylindrical.

4. The aircraft landing gear outer cylinder disassembly and assembly auxiliary device according to claim 1, characterized in that: The roller has a sleeve hole in the middle, and the roller is sleeved on the support rod through the sleeve hole.

5. The aircraft landing gear outer cylinder disassembly and assembly auxiliary device according to claim 1, characterized in that: The roller is provided with a groove for the pull rope to pass through.

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