Aircraft main landing gear axle taking-out device

Abstract

The utility model discloses an aircraft main undercarriage axle taking-out device which comprises a fixing assembly and a driving force transmission assembly, and the fixing assembly extends into a spring tube and is clamped and fixed in the spring tube; the driving force transmission assembly comprises a hydraulic puller and a force transmission part, the force transmission part is arranged between the hydraulic puller and the fixing assembly, a clamping jaw of the hydraulic puller is tensioned on the end face of the axle, and a push rod of the hydraulic puller abuts against the force transmission part. The main landing gear axle dismounting device greatly reduces damage to a main landing gear axle by a traditional maintenance means, improves economical efficiency and safety, is small, flexible and convenient to operate, improves maintenance efficiency, reduces labor intensity of workers, is suitable for dismounting of aircraft axles, and can achieve convenient axle dismounting work.

Description

Technical Field

[0001] This utility model relates to the field of aerospace technology, and in particular to a device for removing the main landing gear axle of an aircraft. Background Technology

[0002] For aircraft with fixed landing gear structures (mainly airplanes), the main wheels are mounted on the spring tubes under the fuselage. Due to factors such as structure, materials, manufacturing process, use, and maintenance, the aircraft landing gear may experience cracks, corrosion, tire bursts, shimmy, brake failure, or even landing gear breakage during landing roll. According to maintenance technical requirements, the main landing gear wheels must be disassembled and inspected during scheduled aircraft structural inspections. The wheel axle, as an important support component of the wheels and a major component connecting the wheel hub and the main landing gear spring tubes, will be the focus of inspection and data measurement.

[0003] During the structural maintenance cycle, aircraft wheel axles undergo numerous takeoffs and landings, and are subjected to multiple complex load changes. Before inspecting the wheel axles, they must be removed from the landing gear spring tubes. Because the wheel axles and spring tubes are interference-fitted, and because the wheels are exposed to high temperature and high humidity air for a long time, the surface of the landing gear spring tubes is prone to corrosion. The reduction in the fit clearance and the stress deformation of the wheel axles make wheel axle disassembly extremely difficult.

[0004] The traditional method of disassembling wheel axles involves using a thick aluminum rod to hold the axle support against its thick edge, then using a copper hammer to repeatedly and forcefully strike the rod along all edges. This repeated striking slowly detaches the axle from the spring tube connector. Removing two damaged axles often requires two adult men working continuously for 2-3 hours. This method is time-consuming, labor-intensive, and prone to deforming the axle edges and causing personal injury. It is also unsafe and inefficient. Utility Model Content

[0005] The purpose of this utility model is to overcome the shortcomings of the prior art and provide an aircraft main landing gear axle removal device, which greatly reduces the damage to the main landing gear axle caused by traditional maintenance methods, improves economy and safety, is small, flexible and easy to operate, improves maintenance efficiency and reduces the labor intensity of personnel, is suitable for aircraft axle disassembly, and can realize convenient axle disassembly work.

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

[0007] An aircraft main landing gear axle removal device includes a fixing component and a drive transmission component, wherein the fixing component extends into the axle and abuts against the end face of the spring tube;

[0008] The drive force transmission assembly includes a hydraulic puller and a force transmission component. The force transmission component is disposed between the hydraulic puller and the fixing assembly. The claws of the hydraulic puller are tightened on the end face of the bearing, and the push rod of the hydraulic puller is pressed against the force transmission component.

[0009] Furthermore, the fixing component includes an expansion inlet and an expansion outlet. The expansion inlet includes a connecting seat. The first end of the connecting seat is provided with multiple expansion flaps. The multiple expansion flaps form an openable and closable expansion tube. The expansion tube is provided with an expansion hole inside. The end of the expansion hole away from the connecting seat is an arc-shaped structure with a gradually decreasing size.

[0010] The connector has a threaded hole inside;

[0011] The first end of the expansion fitting is provided with an external thread that matches the threaded hole, and the second end of the expansion fitting is a cylindrical structure that matches the diameter of the expansion hole circular section.

[0012] Furthermore, an arc-shaped plate is provided at the end of the expansion petal away from the connecting seat, and the arc-shaped plates of multiple expansion petals form a central ring.

[0013] Furthermore, the first end of the expansion joint is provided with a gasket, the outer diameter of which is larger than the diameter of the threaded hole.

[0014] Furthermore, the force transmission component includes a sleeve and a top cover. The sleeve is coaxially sleeved outside the connecting seat, and the top cover is coaxially sleeved outside the connecting seat. The expansion head and expansion tail are located inside the sleeve and the top cover.

[0015] Furthermore, the end of the top cover away from the sleeve is closed to form a force-bearing end face.

[0016] Furthermore, the connecting seat has a regular polygonal structure, and the sleeve and the top cover are both provided with regular polygonal holes that are adapted to the connecting seat.

[0017] Furthermore, the connecting seat has a hexagonal structure.

[0018] The beneficial effects of this utility model are:

[0019] This invention greatly reduces the damage to the main landing gear axle caused by traditional maintenance methods, improves economy and safety, is compact and flexible and easy to operate, improves maintenance efficiency and reduces the labor intensity of personnel, and is applicable to aircraft axle disassembly, enabling convenient axle disassembly work. Attached Figure Description

[0020] Figure 1 This is an exploded view of the aircraft main landing gear axle removal device in an embodiment of this utility model;

[0021] Figure 2A side view of the main landing gear axle removal device for an aircraft.

[0022] Figure 3 for Figure 2 Sectional view along line AA;

[0023] Figure 4 Diagram showing the operational status of the aircraft's main landing gear axle removal device;

[0024] In the diagram, 1. Fixed component; 2. Drive force transmission component; 3. Hydraulic puller; 4. Force transmission component; 5. Wheel axle; 6. Expansion opening; 7. Expansion sleeve; 8. Connecting seat; 9. Expansion flap; 10. Arc plate; 11. Gasket; 12. Sleeve; 13. Top cover; 14. Bourdon tube; 15. Expansion hole. Detailed Implementation

[0025] The technical solution of this utility model will be clearly and completely described below with reference to the embodiments. Obviously, the described embodiments are only some embodiments of this utility model, and not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of this utility model.

[0026] See Figures 1-4 This utility model provides a technical solution: Example

[0027] like Figures 1-4 As shown, an aircraft main landing gear axle removal device includes a fixing component 1 and a drive transmission component 2. The fixing component 1 extends into the axle 5 and abuts (the top post after expansion) against the end face of the spring tube 14. The drive transmission component 2 includes a hydraulic puller 3 and a transmission element 4. The transmission element 4 is disposed between the hydraulic puller 3 and the fixing component 1. The claws of the hydraulic puller 3 are tightened against the end face of the bearing 5, and the push rod of the hydraulic puller 3 abuts against the transmission element 4.

[0028] like Figure 1 and Figure 3 As shown, the fixing component 1 includes an expansion head 6 and an expansion arm 7. The expansion head 6 includes a connecting seat 8. The first end of the connecting seat 8 is provided with a plurality of expansion flaps 9. The plurality of expansion flaps 9 form an openable and closable expansion tube. The expansion tube is provided with an expansion hole 15 inside. The end of the expansion hole 15 away from the connecting seat 8 is an arc-shaped structure with a gradually decreasing size.

[0029] The connector 8 has a threaded hole inside;

[0030] The first end of the expansion fitting 7 is provided with an external thread adapted to the threaded hole, and the second end of the expansion fitting 7 is a cylindrical structure adapted to the diameter of the circular hole section of the expansion opening 15. The expansion fitting 7 is threadedly connected to the connecting seat 8, allowing the expansion fitting 7 to stop at any position to ensure that the expansion opening 6 remains in the expanded state.

[0031] An arc-shaped plate 10 is provided at the end of the expansion petal 9 away from the connecting seat 8, and the arc-shaped plates 10 of multiple expansion petals 9 form an intermediate ring.

[0032] The first end of the expansion joint 7 is provided with a washer, and the outer diameter of the washer 11 is larger than the diameter of the threaded hole. The washer 11 can prevent the expansion joint 7 from moving excessively.

[0033] The force transmission component 4 includes a sleeve 12 and a top cover 13. The sleeve 12 is coaxially sleeved outside the connecting seat 8, and the top cover 13 is coaxially sleeved outside the connecting seat 8. The expansion head 6 and expansion tail 7 are located inside the sleeve 12 and the top cover 13.

[0034] The end of the top cover 13 away from the sleeve 12 is closed to form a force-bearing end face.

[0035] The connecting seat 8 has a regular polygonal structure, and both the sleeve 12 and the top cover 13 have regular polygonal holes that fit the connecting seat 8. The connecting seat 8 has a hexagonal structure. This design is to prevent the force transmission component 4 from rotating under force, which would affect its use.

[0036] Among them, the hydraulic puller 3 is existing technology, and its structure and working principle will not be described in detail here.

[0037] Working principle: Before removing the landing gear axle of the aircraft, the brake bracket, axle through screw and other related components of the axle are removed. The expansion end of the wheel removal tool is inserted into the axle and wedged into the gap of about 3mm between the axle and the landing gear spring tube 14.

[0038] When the expansion sleeve 7 is rotated and screwed in, its second end enters the end of the expansion hole 15. As the size of the end of the expansion hole 15 gradually decreases, multiple expansion petals 9 open radially under the action of the expansion sleeve 7 and the expansion hole 15. During this process, the size of the expansion petals 9 (the diameter of the end of the expansion tube away from the connecting seat 8) increases, so they (through the middle ring) press against the end face of the spring tube 14.

[0039] After the fixing component 1 is installed, the sleeve 12 and the top cover 13 are installed outside the connecting seat 8, so that the expansion head 6 and the expansion outlet 7 are located inside the sleeve 12 and the top cover 13 (the middle ring is located outside the sleeve 12).

[0040] After the force transmission component 4 is installed, the claws of the hydraulic puller 3 are tightened onto the end face of the bearing 5; the push rod of the hydraulic puller 3 is pressed against the top cover 13. When the push rod of the hydraulic puller 3 applies axial force, it is transmitted to the end face of the spring tube 14 through the top cover 13, sleeve 12, and fixing component 1; however, the fixing component 1, the end face of the spring tube, and the limit of the push rod prevent axial displacement. Therefore, the claws pull the bearing 5 to move, and the stroke end of the hydraulic puller 3 and the push rod are repeatedly adjusted. The wheel axle can be removed from the spring tube by using the puller.

[0041] This invention greatly reduces the damage to the main landing gear axle caused by traditional maintenance methods, improves economy and safety, is compact and flexible and easy to operate, improves maintenance efficiency and reduces the labor intensity of personnel, and is applicable to aircraft axle disassembly, enabling convenient axle disassembly work.

[0042] The above description is merely a preferred embodiment of this utility model. It should be understood that this utility model is not limited to the forms disclosed herein and should not be construed as excluding other embodiments. It can be used in various other combinations, modifications, and environments, and can be altered within the scope of the concept described herein through the above teachings or related technologies or knowledge. Modifications and variations made by those skilled in the art that do not depart from the spirit and scope of this utility model should be protected within the scope of the appended claims.

Claims

1. A device for removing the main landing gear axle of an aircraft, characterized in that: It includes a fixing component and a drive transmission component, wherein the fixing component extends into the wheel axle and abuts against the end face of the spring tube of the main landing gear; The drive force transmission assembly includes a hydraulic puller and a force transmission component. The force transmission component is disposed between the hydraulic puller and the fixing assembly. The pawl of the hydraulic puller is tightened on the end face of the wheel axle, and the push rod of the hydraulic puller is pressed against the force transmission component.

2. The aircraft main landing gear axle removal device according to claim 1, characterized in that: The fixing component includes an expansion head and an expansion arm. The expansion head includes a connecting seat. The first end of the connecting seat is provided with multiple expansion flaps. The multiple expansion flaps form an openable and closable expansion tube. The expansion tube is provided with an expansion hole inside. The end of the expansion hole away from the connecting seat is an arc-shaped structure with a gradually decreasing size. The connector has a threaded hole inside; The first end of the expansion fitting is provided with an external thread that matches the threaded hole, and the second end of the expansion fitting is a cylindrical structure that matches the diameter of the expansion hole circular section.

3. The aircraft main landing gear axle removal device according to claim 2, characterized in that: An arc-shaped plate is provided at the end of the expansion flap away from the connecting seat, and the arc-shaped plates of multiple expansion flaps form a central ring.

4. The aircraft main landing gear axle removal device according to claim 2, characterized in that: The first end of the expansion joint is provided with a gasket, the outer diameter of which is larger than the diameter of the threaded hole.

5. The aircraft main landing gear axle removal device according to claim 2, characterized in that: The force transmission component includes a sleeve and a top cover. The sleeve is coaxially sleeved outside the connecting seat, and the top cover is coaxially sleeved outside the connecting seat. The expansion head and expansion tail are located inside the sleeve and the top cover.

6. The aircraft main landing gear axle removal device according to claim 5, characterized in that: The end of the top cover away from the sleeve is closed to form a stress-bearing end face.

7. The aircraft main landing gear axle removal device according to claim 5, characterized in that: The connecting seat has a regular polygonal structure, and the sleeve and the top cover are both provided with regular polygonal holes that are adapted to the connecting seat.

8. The aircraft main landing gear axle removal device according to claim 7, characterized in that: The connector has a hexagonal structure.

Images