An aircraft landing gear disassembly device

Abstract

The present application relates to the technical field of aircraft assembly transfer equipment, and particularly relates to a kind of aircraft landing gear dismounting device, comprising: transfer device, holder and assembly module;Holder is movably arranged on the outside of transfer device, for fixedly connected external aircraft landing gear;Assembly module is arranged on holder, assembly module is connected with the main shaft of transfer device, for the fixed connection of main shaft and holder.This device adopts the structure design of independent holder, when dismounting aircraft landing gear, first, holder is fixedly assembled with landing gear, then transfer device is butted with holder;The design effectively reduces the risk of collision damage caused by the device to aircraft landing gear during the dismounting process of aircraft landing gear, solves the deficiencies existing in the prior art.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft assembly transfer equipment, in particular to an aircraft landing gear dismounting device. BACKGROUND

[0002] The aircraft landing gear dismounting device is suitable for a dismounting and transferring auxiliary device used during dismounting, mounting and maintenance of an aircraft landing gear, such as the aircraft landing gear transfer equipment disclosed in the Chinese patent for invention with the authorization announcement number CN215707227U, which comprises a walking platform and a posture adjusting platform. The walking platform comprises a platform base, and a plurality of fork tooth rods are protruded from the side surface of the platform base, and the aircraft landing gear can be arranged on the fork tooth rods. The posture adjusting platform comprises a clamping unit for clamping the aircraft landing gear, and the clamping unit can move in the X-axis, Y-axis and Z-axis directions relative to the walking platform, and the clamping unit can rotate relative to the walking platform around the Y-axis and Z-axis directions. The clamping unit is further connected with a traction chain, and the traction chain can be connected with the aircraft landing gear. The aircraft landing gear can be supported and clamped.

[0003] However, since the transfer equipment has a large self-weight and high motion inertia, a large impact is easily generated on the landing gear during the process of clamping and fixing the aircraft landing gear by the transfer equipment, and then the collision damage between the aircraft landing gear and the local structure of the transfer equipment can be caused, and there is a problem of large operation difficulty of the aircraft landing gear dismounting operation. SUMMARY

[0004] In view of the technical problem of large operation difficulty in the prior art, the present application provides an aircraft landing gear dismounting device, which comprises:

[0005] A transfer device;

[0006] A retaining frame movably arranged on the outside of the transfer device and used for fixedly connecting the external aircraft landing gear;

[0007] An assembly module arranged on the retaining frame, the assembly module being connected with the main shaft of the transfer device and used for fixedly connecting the main shaft and the retaining frame.

[0008] Further, the assembly module comprises:

[0009] An assembly hole formed on the load bearing protrusion of the retaining frame, the main shaft being movably inserted into the assembly hole when the assembly module is fixedly connected with the main shaft and the retaining frame;

[0010] A pair of insertion holes formed on the outer wall of the load bearing protrusion, the pair of insertion holes being in communication with the assembly hole;

[0011] A clamping groove formed on the axial side wall of the main shaft;

[0012] A pair of locking blocks are movably inserted into a pair of sockets. When the assembly module is fixedly connected to the spindle and the cage, the pair of locking blocks are inserted into the slots to perform axial positioning of the spindle.

[0013] Furthermore, the mounting hole is a prism, and the inner cavity shape of the mounting hole matches the shape of the spindle.

[0014] Furthermore, when a pair of locking blocks are inserted into the slot, the cavity formed by the locking notches of the pair of locking blocks is prism-shaped, and the inner surface of the locking notch fits against the inner wall of the slot.

[0015] Furthermore, the device also includes a buffer module, which is mounted on the cage and connected to the spindle for buffering the spindle.

[0016] Furthermore, the buffer module includes:

[0017] The receiving groove is formed on the end face of the bearing protrusion facing the aircraft landing gear, and the receiving groove is connected to the mounting hole.

[0018] The telescopic cylinder is movably installed in the inner cavity of the receiving groove. The telescopic cylinder is slidably connected to the inner wall of the receiving groove. When the assembly module is fixedly connected to the spindle and the cage, the telescopic cylinder is connected to the spindle.

[0019] A pair of elastic support components are mounted on the cage. The pair of elastic support components are connected to a pair of locking blocks respectively, and the pair of elastic support components are connected to the telescopic cylinder.

[0020] Furthermore, the resilient support component includes:

[0021] The fixing block is fixedly mounted on the retainer;

[0022] The movable rod is movably inserted into one of the sockets. The head end of the movable rod is fixedly connected to the corresponding locking block, and the movable rod is slidably connected to the fixed block.

[0023] A limiting protrusion is fixedly mounted on the movable rod, and the limiting protrusion is located between the insertion hole and the fixed block;

[0024] The slider is movably sleeved on the movable rod, and the slider is slidably connected to the movable rod along the axial direction of the movable rod. The slider is located between the limiting protrusion and the fixed block.

[0025] A support spring is movably sleeved on the movable rod. One end of the support spring is connected to the limiting protrusion, and the other end of the support spring is connected to the slider.

[0026] The connecting rod has one end hinged to the slider and the other end hinged to the telescopic cylinder, and is used to drive the slider to slide along the axis of the movable rod.

[0027] Furthermore, the resilient support component also includes:

[0028] The first permanent magnet is fixedly mounted on the cage;

[0029] A transmission protrusion is fixedly installed at the tail end of the movable rod. The position of the transmission protrusion corresponds to that of the first permanent magnet. The transmission protrusion is a magnetic metal part used to drive the movable rod to slide and reset.

[0030] Furthermore, the telescopic cylinder includes:

[0031] The cylinder is movably disposed in the receiving groove, and the cylinder is slidably connected to the inner wall of the receiving groove. The end of the cylinder facing the aircraft landing gear is connected to a pair of elastic support components.

[0032] The piston is movably disposed in the inner cavity of the cylinder, and the circumferential sidewall of the piston is in close contact with the circumferential inner wall of the cylinder.

[0033] The externally threaded tube is fixedly installed on the end face of the cylinder body facing the aircraft landing gear, and the tail end of the externally threaded tube is connected to the inner cavity of the cylinder body.

[0034] A rigid bearing plate is fixedly mounted on the end face of the piston facing away from the external threaded tube. When the assembly module is fixedly connected to the spindle and the cage, the rigid bearing plate abuts against the spindle.

[0035] End cap, fastened to the head end of the externally threaded pipe, is threadedly connected to the externally threaded pipe;

[0036] The second permanent magnet is fixedly installed inside the piston, and the main shaft is a magnetic metal component.

[0037] An aircraft landing gear removal device according to an embodiment of the present invention has the following advantages:

[0038] 1. This device adopts an independent cage structure design. When disassembling the aircraft landing gear, the cage is first fixedly assembled with the landing gear, and then the transfer device is connected to the cage. This design effectively reduces the risk of collision damage to the aircraft landing gear during the disassembly process and solves the shortcomings of the existing technology.

[0039] 2. This device uses an elastic support component to buffer the main shaft, thereby further reducing the impact of the transfer device on the aircraft landing gear during the docking process between the transfer device and the cage. At the same time, it also converts part of the impact force applied to the main shaft into elastic potential energy, providing preload force for the locking block and the main shaft, which helps to stabilize the locking block and the locking slot and enhances the structural stability of this device.

[0040] 3. This device uses a telescopic cylinder to connect the main shaft and the elastic support assembly. This allows the user to remove the end cover and allow the gas inside the cylinder to be discharged through the external threaded pipe, thereby releasing the elastic potential energy of the support spring. This allows the movable rod to drive the locking block to slide and reset under the magnetic force of the first permanent magnet, releasing the locking block from the main shaft. This makes it easy for the user to separate the transfer device from the cage, enhancing the ease of use of this device.

[0041] It should be understood that both the foregoing general description and the following detailed description are exemplary and intended to provide further illustration of the claimed technology. Attached Figure Description

[0042] Figure 1 This is a perspective view according to an embodiment of the present invention;

[0043] Figure 2 This is an assembly diagram according to an embodiment of the present invention;

[0044] Figure 3 This is a schematic diagram of the internal structure of the bearing protrusion according to an embodiment of the present invention;

[0045] Figure 4 A part drawing of a card block according to an embodiment of the present invention;

[0046] Figure 5 A part drawing of a spindle according to an embodiment of the present invention;

[0047] Figure 6 for Figure 2 A magnified view of a portion of region A in the middle.

[0048] Explanation of reference numerals in the attached figures:

[0049] 1-Transfer device, 11-Main shaft, 2-Cage, 21-Bearing protrusion, 31-Assembly hole, 32-Insertion hole, 33-Slot, 34-Clocking block, 341-Clocking notch, 4-Buffer module, 41-Accommodation groove, 42-Elastic support assembly, 421-Fixing block, 422-Moving rod, 423-Limiting protrusion, 424-Slider, 425-Supporting spring, 426-Connecting rod, 427-First permanent magnet, 428-Transmission protrusion, 43-Telescopic cylinder, 431-Cylinder body, 432-Piston, 433-External threaded tube, 434-Hard bearing plate, 435-End cap, 436-Second permanent magnet. Detailed Implementation

[0050] The preferred embodiments of the present invention will be described in detail below with reference to the accompanying drawings, further illustrating the present invention.

[0051] The foregoing and other technical contents, features, and effects of the present invention will become clear in the following detailed description of the embodiments with reference to the accompanying drawings. Furthermore, in all embodiments, the same reference numerals denote the same elements.

[0052] First, combine Figures 1-6 This invention describes an aircraft landing gear disassembly device according to an embodiment of the present invention, which is used for the disassembly, assembly, and transfer of aircraft landing gear and has a wide range of applications.

[0053] Specifically, such as Figures 1-5 As shown, the present invention proposes an aircraft landing gear disassembly device, comprising: a transfer device 1, a retainer 2, and an assembly module; the retainer 2 is movably disposed on the outside of the transfer device 1 for fixing the external aircraft landing gear; the assembly module is disposed on the retainer 2 and is connected to the main shaft 11 of the transfer device 1 for fixing the main shaft 11 to the retainer 2.

[0054] Furthermore, such as Figures 1-5 As shown, the assembly module includes: an assembly hole 31, a pair of insertion holes 32, a slot 33, and a pair of locking blocks 34. The assembly hole 31 is formed on the bearing protrusion 21 of the cage 2. When the assembly module is fixedly connected to the spindle 11 and the cage 2, the spindle 11 is movably inserted into the assembly hole 31. The pair of insertion holes 32 are formed on the outer wall of the bearing protrusion 21, and both insertion holes 32 are connected to the assembly hole 31. The slot 33 is formed on the axial side wall of the spindle 11. The pair of locking blocks 34 are movably inserted into the pair of insertion holes 32. When the assembly module is fixedly connected to the spindle 11 and the cage 2, the pair of locking blocks 34 are inserted into the slot 33 for axial positioning of the spindle 11.

[0055] Furthermore, such as Figures 1-5 As shown, the mounting hole 31 is a prism, and the inner cavity shape of the mounting hole 31 matches the shape of the spindle 11 to increase the bearing area of ​​the spindle 11 and reduce the local load on the spindle 11 during the process of controlling the spindle 11 to adjust the deflection angle of the cage 2.

[0056] Furthermore, such as Figures 1-5 As shown, when a pair of locking blocks 34 are inserted into the slot 33, the cavity formed by the locking notches 341 of the pair of locking blocks 34 is prism-shaped. The inner surface of the locking notches 341 fits against the inner wall of the slot 33 to increase the bearing area of ​​the spindle 11 and reduce the local load on the spindle 11 during the process of controlling the spindle 11 to adjust the deflection angle of the retainer 2.

[0057] Furthermore, the device also includes a buffer module 4, which is mounted on the cage 2 and connected to the spindle 11 for buffering the spindle 11.

[0058] Furthermore, such asFigures 1-5 As shown, the buffer module 4 includes: a receiving groove 41, a telescopic cylinder 43, and a pair of elastic support components 42; the receiving groove 41 is formed on the end face of the bearing protrusion 21 facing the aircraft landing gear, and the receiving groove 41 is connected to the mounting hole 31; the telescopic cylinder 43 is movably disposed in the inner cavity of the receiving groove 41, and the telescopic cylinder 43 is slidably connected to the inner wall of the receiving groove 41. When the assembly module is fixedly connected to the main shaft 11 and the retainer 2, the telescopic cylinder 43 is connected to the main shaft 11; the pair of elastic support components 42 are disposed on the retainer 2, and the pair of elastic support components 42 are respectively connected to a pair of locking blocks 34, and the pair of elastic support components 42 are connected to the telescopic cylinder 43.

[0059] Furthermore, such as Figures 1-5 As shown, the elastic support assembly 42 includes: a fixed block 421, a movable rod 422, a limiting protrusion 423, a slider 424, a support spring 425, and a connecting rod 426; the fixed block 421 is fixedly mounted on the retainer 2; the movable rod 422 is movably inserted into one of the insertion holes 32, the head end of the movable rod 422 is fixedly connected to the corresponding locking block 34, and the movable rod 422 is slidably connected to the fixed block 421; the limiting protrusion 423 is fixedly mounted on the movable rod 422, and the limiting protrusion 423 is located between the insertion hole 32 and the fixed block 421; the slider 424... The slider 424 is slidably connected to the movable rod 422 along the axial direction of the movable rod 422, and is located between the limiting protrusion 423 and the fixed block 421. The support spring 425 is slidably mounted on the movable rod 422, with one end of the support spring 425 connected to the limiting protrusion 423 and the other end of the support spring 425 connected to the slider 424. One end of the connecting rod 426 is hinged to the slider 424, and the other end of the connecting rod 426 is hinged to the telescopic cylinder 43, which is used to drive the slider 424 to slide along the axial direction of the movable rod 422.

[0060] Furthermore, such as Figures 1-5 As shown, the elastic support assembly 42 also includes: a first permanent magnet 427 and a transmission protrusion 428; the first permanent magnet 427 is fixedly mounted on the retainer 2; the transmission protrusion 428 is fixedly mounted on the tail end of the movable rod 422, the position of the transmission protrusion 428 corresponds to that of the first permanent magnet, the transmission protrusion 428 is a magnetic metal part, used to drive the movable rod 422 to slide and reset.

[0061] Furthermore, such as Figure 2 , Figure 6As shown, the telescopic cylinder 43 includes: a cylinder body 431, a piston 432, an externally threaded tube 433, a rigid support plate 434, an end cap 435, and a second permanent magnet 436; the cylinder body 431 is movably disposed in the receiving groove 41, and the cylinder body 431 is slidably connected to the inner wall of the receiving groove 41; the end of the cylinder body 431 facing the aircraft landing gear is hinged to the connecting rod 426 of a pair of elastic support assemblies 42; the piston 432 is movably disposed in the inner cavity of the cylinder body 431, and the circumferential sidewall of the piston 432 is tightly fitted with the circumferential inner wall of the cylinder body 431; the externally threaded tube 433 is fixedly disposed on the end face of the cylinder body 431 facing the aircraft landing gear. The tail end of the external threaded tube 433 is connected to the inner cavity of the cylinder 431; the rigid bearing plate 434 is fixedly mounted on the end face of one end of the piston 432, and the piston 432 is located between the rigid bearing plate 434 and the external threaded tube 433. When the assembly module is fixedly connected to the spindle 11 and the cage 2, the rigid bearing plate 434 abuts against the head end of the spindle 11; the end cap 435 is fastened to the head end of the external threaded tube 433, and the end cap 435 is threadedly connected to the external threaded tube 433; the second permanent magnet 436 is fixedly mounted inside the piston 432, and the second permanent magnet 436 is fixedly connected to the rigid bearing plate 434. The spindle 11 is a magnetic metal part.

[0062] When a user uses this device to disassemble an aircraft landing gear, firstly, the user uses the latches on the retainer 2 to securely connect the retainer 2 to the aircraft landing gear strut. Then, the user pushes the transfer device 1, causing the main shaft 11 of the transfer device 1 to insert into the assembly hole 31. As the insertion depth of the main shaft 11 increases, after the head end of the main shaft 11 contacts the rigid support plate 434 of the telescopic cylinder 43, the main shaft 11 pushes the rigid support plate 434 to drive the cylinder body 431 to extend out of the receiving groove 41. As the cylinder body 431 extends out of the receiving groove 41, the cylinder body 431 drives the slider 424 to slide towards the bearing protrusion 21 via the connecting rod 426. The slider 424 cooperates with the limiting protrusion 423 to support the spring 42. 5. Compression, thereby using the support spring 425 to buffer the main shaft 11, so as to reduce the impact of the transfer device 1 on the cage 2 and the aircraft landing gear fixedly connected to the cage 2; as the depth of the main shaft 11 inserted into the assembly hole 31 increases, when the slot 33 provided on the main shaft 11 is displaced to the position corresponding to a pair of insertion holes 32, the movable rod 422 overcomes the magnetic force between the first permanent magnet 427 and the transmission protrusion 428 under the elastic drive of the support spring 425, and drives the locking block 34 to snap onto the main shaft 11 and engage with the slot 33, thereby locking the main shaft 11 in the assembly hole 31, and realizing the purpose of fixing and assembling the cage 2, which is fixedly connected to the aircraft landing gear, and the main shaft 11 of the transfer device 1.

[0063] When the user needs to release the fixed assembly between the transfer device 1 and the retainer 2, the user can remove the end cap 435 from the external threaded tube 433, allowing the air inside the cylinder 431 to be expelled through the external threaded tube 433. This allows the cylinder 431 to retract into the receiving groove 41 under the elastic force of the support spring 425, keeping the piston 432 in its original position. This releases the elastic potential energy of the support spring 425 and reduces the frictional resistance between the main shaft 11 and the locking block 34. Then, the movable rod 422, under the magnetic force between the first permanent magnet 427 and the transmission protrusion 428, drives the locking block 34 out of the slot 3. 3. The main spindle 11 is released from the mounting hole 31 by disengaging the locking block 34. Finally, the user drives the transfer device 1 to move backward and pull the main spindle 11 out of the mounting hole 31 to release the fixed assembly state between the transfer device 1 and the cage 2. In addition, during the process of the transfer device 1 driving the main spindle 11 out of the mounting hole 31, the piston 432 and the rigid support plate 434 set on the piston 432 slide towards the port of the cylinder 431 under the magnetic attraction between the second permanent magnet 436 and the main spindle 11. After sliding to the port of the cylinder 431, the main spindle 11 separates from the rigid support plate 434 under the action of external force.

[0064] Above, refer to Figures 1-6 An aircraft landing gear removal device according to an embodiment of the present invention is described, which has the following beneficial effects:

[0065] 1. This device adopts an independent cage 2 structure design. When disassembling the aircraft landing gear, the cage 2 is first fixedly assembled with the landing gear, and then the transfer device 1 is connected to the cage 2. This design effectively reduces the risk of collision damage to the aircraft landing gear during the disassembly process and solves the shortcomings of the existing technology.

[0066] 2. This device uses an elastic support component 42 to buffer the main shaft 11, thereby further reducing the impact of the transfer device 1 on the aircraft landing gear during the docking process between the transfer device 1 and the cage 2. At the same time, it also converts part of the impact force applied to the main shaft 11 into elastic potential energy, providing pre-tightening force for the locking block 34 and the main shaft 11, which helps the locking block 34 and the locking groove 33 to be locked stably, thus enhancing the structural stability of this device.

[0067] 3. This device uses a telescopic cylinder 43 to connect the main shaft 11 and the elastic support assembly 42. This allows the user to remove the end cover 435 to allow the gas in the cylinder 431 to be discharged through the external threaded pipe 433, thereby releasing the elastic potential energy of the support spring 425. This allows the movable rod 422 to drive the locking block 34 to slide and reset under the magnetic force of the first permanent magnet 427, releasing the locking block 34 from the main shaft 11. This makes it easier for the user to separate the transfer device 1 from the cage 2, thus enhancing the ease of use of this device.

[0068] It should be noted that, in this specification, the terms "comprising," "including," or any other variations thereof are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0069] Although the present invention has been described in detail through the preferred embodiments above, it should be understood that the above description should not be considered as a limitation of the present invention. Various modifications and substitutions to the present invention will be apparent to those skilled in the art after reading the above description. Therefore, the scope of protection of the present invention should be defined by the appended claims.

Claims

1. An aircraft landing gear disassembly device, characterized in that, Include: Transfer device; A retainer, movably mounted on the outside of the transfer device, is used to securely connect to the external aircraft landing gear; An assembly module is disposed on the cage and is connected to the main shaft of the transfer device for fixing the main shaft to the cage. The assembly module includes: An assembly hole is formed on the bearing protrusion of the cage. When the assembly module is fixedly connected to the spindle and the cage, the spindle is movably inserted into the assembly hole. A pair of insertion holes are provided on the outer wall of the supporting protrusion, and both of the pair of insertion holes communicate with the assembly hole; A slot is formed on the axial side wall of the spindle; A pair of locking blocks are respectively movably inserted into the pair of sockets. When the assembly module is fixedly connected to the spindle and the cage, the pair of locking blocks are inserted into the slots to perform axial positioning of the spindle. It also includes: a buffer module, which is disposed on the cage and connected to the spindle for buffering the spindle; The buffer module includes: A receiving groove is formed on the end face of the bearing protrusion facing the end of the aircraft landing gear, and the receiving groove communicates with the mounting hole; A telescopic cylinder is movably disposed in the inner cavity of the receiving groove. The telescopic cylinder is slidably connected to the inner wall of the receiving groove. When the assembly module is fixedly connected to the main shaft and the cage, the telescopic cylinder is connected to the main shaft. A pair of elastic support components are disposed on the retainer, the pair of elastic support components are respectively connected to the pair of locking blocks, and the pair of elastic support components are connected to the telescopic cylinder; The elastic support component includes: The fixing block is fixedly mounted on the retainer; A movable rod is movably inserted into one of the sockets, the head end of the movable rod is fixedly connected to the corresponding locking block, and the movable rod is slidably connected to the fixed block; A limiting protrusion is fixedly mounted on the movable rod, and the limiting protrusion is located between the insertion hole and the fixed block; A slider is movably sleeved on the movable rod, and the slider is slidably connected to the movable rod along the axial direction of the movable rod. The slider is located between the limiting protrusion and the fixed block. A support spring is movably sleeved on the movable rod. One end of the support spring is connected to the limiting protrusion, and the other end of the support spring is connected to the slider. A connecting rod, one end of which is hinged to the slider and the other end of which is hinged to the telescopic cylinder, is used to drive the slider to slide along the axial direction of the movable rod.

2. The aircraft landing gear disassembly device as described in claim 1, characterized in that, The mounting hole is a prism, and the inner shape of the mounting hole matches the shape of the spindle.

3. The aircraft landing gear removal device as described in claim 1, characterized in that, When the pair of locking blocks are inserted into the slot, the cavity formed by the locking notches of the pair of locking blocks is prism-shaped, and the inner surface of the locking notch fits against the inner wall of the slot.

4. The aircraft landing gear disassembly device as described in claim 1, characterized in that, The elastic support component further includes: The first permanent magnet is fixedly mounted on the cage; A transmission protrusion is fixedly disposed at the tail end of the movable rod. The transmission protrusion corresponds to the position of the first permanent magnet. The transmission protrusion is a magnetic metal part and is used to drive the movable rod to slide and reset.

5. The aircraft landing gear disassembly device as described in claim 1, characterized in that, The telescopic cylinder includes: The cylinder is movably disposed in the receiving groove, the cylinder is slidably connected to the inner wall of the receiving groove, and the end of the cylinder facing the aircraft landing gear is connected to the pair of elastic support assemblies. The piston is movably disposed in the inner cavity of the cylinder, and the circumferential sidewall of the piston is in close contact with the circumferential inner wall of the cylinder; An externally threaded tube is fixedly installed on the end face of the cylinder body facing the aircraft landing gear, and the tail end of the externally threaded tube is connected to the inner cavity of the cylinder body. A rigid bearing plate is fixedly disposed on the end face of the piston facing away from the external threaded tube. When the assembly module is fixedly connected to the spindle and the cage, the rigid bearing plate abuts against the spindle. An end cap is fastened to the head end of the externally threaded pipe, and the end cap is threadedly connected to the externally threaded pipe. The second permanent magnet is fixedly installed inside the piston, and the main shaft is a magnetic metal component.

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