Disassembling and assembling vehicle for main landing gear of airplane

Abstract

The utility model provides a disassembling and assembling vehicle for an aircraft main landing gear, which belongs to the technical field of aviation maintenance, and adopts the technical scheme that the disassembling and assembling vehicle for the aircraft main landing gear comprises a chassis, a lifting platform and a driving mechanism are arranged on the chassis, the driving mechanism can drive the lifting platform to ascend and descend, a supporting disc is fixed on the lifting platform, and the supporting disc is fixed on the chassis. A rotating disc is installed on the supporting disc and rotationally connected with the supporting disc, an installation frame is further fixed to the lifting table, a limiting ring is fixed to the top of the installation frame, and a guide wheel is installed on the inner wall of the limiting ring. The main landing gear adjusting device has the advantages that the height of the main landing gear of the aircraft can be accurately adjusted, more importantly, the direction of the main landing gear of the aircraft can be easily and flexibly adjusted without rotating the chassis, the operation convenience degree is greatly improved, the maintenance operation efficiency is remarkably improved, and the maintenance cost is reduced. And great convenience is brought to the maintenance work of the main landing gear of the aircraft.

Description

Technical Field

[0001] This utility model belongs to the field of aviation maintenance technology, specifically relating to a disassembly and assembly vehicle for aircraft main landing gear. Background Technology

[0002] In routine aircraft maintenance and repair, disassembly and assembly vehicles play a crucial role. The main landing gear, as a core component supporting the aircraft and absorbing landing impacts during takeoff and landing, requires frequent and complex repair and replacement. With the help of specialized disassembly and assembly vehicles, the main landing gear can be installed and removed efficiently and safely, greatly improving aircraft maintenance efficiency and ensuring flight safety.

[0003] Currently, common aircraft main landing gear assembly and disassembly vehicles include a base with casters at the bottom. Above the base is a lifting platform, which plays a crucial role in supporting the aircraft's main landing gear. Its lifting function typically relies on hydraulic systems or lead screw and nut drives. These mature lifting technologies allow for relatively stable adjustment of the aircraft's main landing gear height, meeting the height requirements in different maintenance scenarios and providing maintenance personnel with a suitable operating height.

[0004] However, aircraft main landing gear maintenance requires not only height adjustment but also, in many cases, directional adjustment. Existing disassembly and assembly vehicles can only achieve directional adjustment of the main landing gear by rotating the base with casters. In actual airport maintenance environments, space is often limited, and various equipment, tools, and other aircraft components are present, preventing the disassembly and assembly vehicle from rotating freely. Furthermore, ground conditions are not always flat and smooth, and may include potholes, slopes, etc., further limiting the effectiveness of directional adjustment using the casters. This limitation in directional adjustment seriously affects the efficiency and quality of maintenance work. Utility Model Content

[0005] This invention addresses the problem that existing disassembly and assembly vehicles are inconvenient for adjusting the direction of aircraft main landing gear, and provides an aircraft main landing gear disassembly and assembly vehicle that facilitates the direction adjustment of aircraft main landing gear.

[0006] To solve the above problems, the technical solution adopted by this utility model is as follows: a disassembly and assembly vehicle for aircraft main landing gear, including a chassis, a lifting platform provided on the chassis, a drive mechanism provided on the chassis, the drive mechanism can drive the lifting platform to lift and lower, a support plate fixed on the lifting platform, a rotating plate installed on the support plate, the rotating plate being rotatably connected to the support plate, an installation frame fixed on the lifting platform, a limit ring fixed on the top of the installation frame, and guide wheels installed on the inner wall of the limit ring.

[0007] In this technical solution, the rotating disk bears the crucial responsibility of supporting the aircraft's main landing gear, while the limiting ring functions to limit the main landing gear, ensuring it remains in a vertical position. The drive mechanism, aided by the lifting platform, allows for precise height adjustment of the main landing gear; the rotating disk, through its own rotation, facilitates convenient direction adjustment of the main landing gear. Simultaneously, guide wheels on the inner wall of the limiting ring provide auxiliary support for the rotation of the main landing gear. In summary, this solution not only possesses the capability to adjust the height of the aircraft's main landing gear, but more importantly, it allows for easy and flexible direction adjustment of the main landing gear without rotating the chassis, greatly improving operational convenience and efficiency.

[0008] Furthermore, a guide rod is installed on the chassis, with its bottom fixedly connected to the chassis, a handrail fixed to its top, and a fixing block fixed to its middle. The fixed handrail at the top provides a convenient grip for the operator. When moving the disassembly and assembly vehicle, the operator can easily exert force by gripping the handrail to control the vehicle's direction and speed. This design enhances the convenience and flexibility of operation, especially in confined spaces or maintenance environments requiring precise adjustments.

[0009] Furthermore, the drive mechanism includes a hydraulic actuator, the cylinder of which is fixed to the chassis. A connecting shaft is fixed to the end of the telescopic rod of the hydraulic actuator, and rollers are rotatably connected to both ends of the connecting shaft. A chain is wrapped around the top of the rollers, one end of which is fixedly connected to a fixed block, and the other end of which is fixedly connected to the lifting platform. The rollers are connected to the telescopic rod of the hydraulic actuator via the connecting shaft. The rollers are wrapped around the chain and connected to the fixed block and the lifting platform through the chain, forming a transmission system. When the telescopic rod of the hydraulic actuator extends or retracts, it drives the connecting shaft and rollers to move, effectively converting the linear motion of the hydraulic actuator into the cyclic motion of the chain, thereby precisely controlling the lifting action of the lifting platform and achieving efficient power transmission and conversion.

[0010] Furthermore, the end of the telescopic rod of the hydraulic actuator is fixedly connected to the middle of the connecting shaft, which is horizontally positioned. This horizontal connecting shaft helps keep the rollers on the same horizontal plane, reducing the up-and-down fluctuations and swaying of the chain during transmission. This is crucial for controlling the lifting platform's ascent and descent, ensuring smooth operation and preventing tilting or swaying caused by uneven chain transmission. This provides stable support and precise altitude adjustment for the aircraft's main landing gear.

[0011] Furthermore, a limit plate is installed on the side of the lifting platform near the handrail, with two limit blocks fixed to the limit plate, located on both sides of the guide rod. The guide rod and limit blocks work together to create a concealed track for the lifting platform. When the lifting platform rises or falls, the two limit blocks on either side of the guide rod strictly limit the horizontal displacement of the lifting platform, preventing it from swaying, deviating, or twisting, ensuring smooth vertical movement during lifting and lowering, guaranteeing the safety and stability of the aircraft's main landing gear during the process, and preventing damage to the main landing gear due to platform swaying.

[0012] Furthermore, a mounting base is fixed to the lifting platform, and the bottom of the mounting bracket is inserted into the mounting base. In aircraft maintenance areas with limited space, the mounting bracket can be pulled out of the mounting base, reducing the overall size and making the lifting platform easier to move to the target location. Once there, the mounting bracket is inserted back into the mounting base, quickly restoring the load-bearing and operational functions of the aircraft's main landing gear, greatly improving the equipment's adaptability in complex spaces.

[0013] Furthermore, a support rod is installed on the lifting platform. One end of the support rod is fixedly connected to the lifting platform, and the other end is fixedly connected to the middle of the mounting frame. The support rod connects the middle of the lifting platform and the mounting frame, forming a stable triangular structure. This structure effectively distributes the weight borne by the mounting frame and various forces generated during operation, reducing deformation and swaying of the mounting frame. This makes the entire device more stable and reliable during lifting, providing solid support for the aircraft's main landing gear.

[0014] Furthermore, a rotating shaft is installed inside the guide wheel, with its axis pointing vertically. Both ends of the rotating shaft are fixedly connected to the inner wall of the limiting ring. The rotating shaft provides a stable center of rotation for the guide wheel, enabling it to rotate smoothly around its vertical axis. Because both ends of the rotating shaft are fixedly connected to the inner wall of the limiting ring, the displacement of the rotating shaft during the rotation of the guide wheel is restricted, ensuring the stability and reliability of the guide wheel's rotation and reducing swaying and deviation.

[0015] Furthermore, at least three guide wheels are provided, and all guide wheels are evenly distributed at equal angles around the axis of the limiting ring. The even distribution of multiple guide wheels provides more balanced support to the aircraft's main landing gear. This layout effectively resists external forces from different directions, improving the stability and reliability of the entire device under load. Even under significant external forces or impacts, the device maintains structural integrity, reducing the risk of malfunctions or accidents.

[0016] Furthermore, a buffer pad is fixed to the top of the rotating disk. When the aircraft's main landing gear is placed on the rotating disk or when a certain impact force is generated during rotation, the buffer pad can absorb and disperse these impact forces, reduce damage to the rotating disk and the structural components connected to it, and extend the service life of the entire device.

[0017] As can be seen from the above technical solution, the advantages of this utility model are as follows: the rotating disk supports and supports the aircraft's main landing gear, while the limiting ring limits the main landing gear, ensuring it remains vertical. The hydraulic actuator, as a power source, drives the lifting platform via a chain, enabling height adjustment of the aircraft's main landing gear. The rotating disk itself allows for convenient and quick adjustment of the aircraft's main landing gear direction. The guide wheels on the inner wall of the limiting ring assist in the rotation of the main landing gear, reducing rotational resistance and making the rotation process smoother. In summary, this solution not only achieves precise height adjustment of the aircraft's main landing gear, but more importantly, it allows for easy and flexible adjustment of the aircraft's main landing gear direction without rotating the chassis, greatly improving operational convenience, significantly increasing maintenance efficiency, and bringing great convenience to the maintenance of the aircraft's main landing gear. Attached Figure Description

[0018] To more clearly illustrate the technical solution of this utility model, the drawings used in the description will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0019] Figure 1 This is a structural diagram illustrating a specific embodiment of the present invention. Figure 1 ;

[0020] Figure 2 This is a structural diagram illustrating a specific embodiment of the present invention. Figure 2 ;

[0021] Figure 3 This is a structural diagram illustrating a specific embodiment of the present invention. Figure 3 .

[0022] In the diagram: 1-Chassis, 11-Wheel caster, 12-Handrail, 13-Guide rod, 14-Fixing block, 2-Lifting platform, 21-Mounting base, 22-Limiting plate, 23-Limiting block, 3-Mounting frame, 31-Support rod, 4-Support plate, 5-Rotating plate, 51-Buffer pad, 6-Limiting ring, 61-Guide wheel, 62-Rotating shaft, 7-Hydraulic actuator, 71-Connecting shaft, 72-Roller, 73-Chain, 74-Pressure pedal, 75-Pressure relief pedal. Detailed Implementation

[0023] To make the objectives, features, and advantages of this utility model more apparent and understandable, the technical solutions of this utility model will be clearly and completely described below with reference to the accompanying drawings of the specific embodiments. Obviously, the embodiments described below are only some embodiments of this utility model, and not all embodiments. Based on the embodiments of this patent, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this patent.

[0024] A type of aircraft main landing gear disassembly and assembly vehicle, such as Figure 1 As shown, the system includes a chassis 1, on which a lifting platform 2 is mounted, and a drive mechanism is installed. The drive mechanism drives the lifting platform 2 to perform smooth lifting movements according to a predetermined power transmission path. A support plate 4 is fixedly connected to the lifting platform 2. A rotating plate 5 is mounted on the support plate 4, and the rotating plate 5 is rotatably connected to the support plate 4, meaning that the rotating plate 5 can rotate on the support plate 4. Furthermore, a mounting bracket 3 is fixedly installed on the lifting platform 2 at a location away from the drive mechanism, providing auxiliary support for the aircraft's main landing gear.

[0025] In this specific embodiment, the chassis 1 adopts the following structure: Two support wheels are installed on the bottom of one side of the chassis 1, providing support for the chassis 1. Two casters 11 are installed on the bottom of the other side of the chassis 1, facilitating the movement of the chassis 1. A guide rod 13 is provided on the top of the chassis 1 near the casters 11, and the bottom of the guide rod 13 is connected to the chassis 1 by welding. There are a total of two guide rods 13, which are symmetrically distributed along the longitudinal center plane of the chassis 1. The tops of the two guide rods 13 are connected to the handle 12 by welding. In addition, a fixing block 14 is provided between the two guide rods 13, and the two ends of the fixing block 14 are respectively connected to the middle of the two guide rods 13 by welding. A reinforcing rod is provided between the handrail 12 and the chassis 1. One end of the reinforcing rod is connected to the handrail 12 by welding, and the other end of the reinforcing rod is connected to the chassis 1 by welding. A total of two reinforcing rods are provided, and the two reinforcing rods are symmetrically distributed along the longitudinal center plane of the chassis 1. In addition, the two reinforcing rods are respectively welded to two guide rods 13 through reinforcing plates.

[0026] In this specific embodiment, the lifting platform 2 adopts the following structure: The lifting platform 2 includes a base plate and an upright plate. The upright plate is welded to the side of the base plate near the handrail 12, and the upright plate is perpendicular to the base plate. The lifting platform 2 is L-shaped overall. The support plate 4 is welded to the middle position of the lifting platform 2. A slewing bearing is provided between the support plate 4 and the rotating plate 5. The slewing bearing is existing equipment, such as the XRSA series slewing bearing from Luoyang Prisen Precision Bearing Co., Ltd. The inner ring of the slewing bearing is fixedly connected to the support plate 4 by bolts, and the outer ring of the slewing bearing is fixedly connected to the rotating plate 5 by bolts. A buffer pad 51 is fixed to the top of the rotating plate 5 by adhesive bonding.

[0027] The lifting platform 2 is equipped with a mounting base 21. The bottom of the mounting base 21 is connected to the lifting platform 2 by welding. The top of the mounting base 21 has a mounting groove, and the side wall of the mounting groove has threaded holes. The bottom of the mounting bracket 3 has a clear hole, and the bottom of the mounting bracket 3 is inserted into the mounting groove. At this time, the clear hole and the threaded hole are aligned. The mounting bracket 3 can be fixed to the mounting base 21 by bolt connection. There are two mounting bases 21 in total, and the two mounting bases 21 are symmetrically distributed along the longitudinal center plane of the lifting platform 2.

[0028] like Figure 3 As shown, a limit plate 22 is provided on the outer side of the upright plate of the lifting platform 2. The limit plate 22 is triangular in shape, and one right-angled side of the limit plate 22 is connected to the upright plate by welding. In this embodiment, a total of four limit plates 22 are provided. The four limit plates 22 are parallel to each other and divided into two groups. The two groups of limit plates 22 are symmetrically distributed along the longitudinal center plane of the lifting platform 2. In each group, two limit plates 22 clamp a guide rod 13. Two limit blocks 23 are also provided between the two limit plates 22 in each group. The limit blocks 23 are fixedly connected to the limit plates 22 by bolts, and the two limit blocks 23 are located on both sides of the guide rod 13.

[0029] like Figure 2As shown, in this specific embodiment, the drive mechanism adopts the following structure: The drive mechanism includes a hydraulic actuator 7, which is an existing device. The hydraulic actuator 7 is vertically positioned and located between the guide rod 13 and the lifting platform 2. The cylinder body of the hydraulic actuator 7 is connected to the chassis 1 by welding. A pressure pedal 74 and a pressure relief pedal 75 are provided on the cylinder body of the hydraulic actuator 7. When the pressure pedal 74 is pressed, the telescopic rod of the hydraulic actuator 7 extends; when the pressure relief pedal 75 is pressed, the telescopic rod of the hydraulic actuator 7 retracts. The end of the telescopic rod of the hydraulic actuator 7 is connected to the middle of the connecting shaft 71 by welding, and the connecting shaft 71 is horizontally positioned. Bearings are fitted at both ends of the connecting shaft 71, and the inner ring of the bearing is connected to the outer wall of the connecting shaft 71 by an interference fit. Rollers 72 are fitted onto the outer ring of the bearing, and the outer ring of the bearing is connected to the inner wall of the roller 72 by an interference fit. A chain 73 is wrapped around the top of the roller 72. One end of the chain 73 is fixedly connected to the fixing block 14 by bolts, and the other end of the chain 73 is fixedly connected to the upright plate of the lifting platform 2 by bolts.

[0030] In this specific embodiment, the mounting frame 3 adopts the following structure: The mounting frame 3 includes two columns, the tops of which are welded together by a crossbeam, and a cross-shaped reinforcing beam is welded between the two columns. Each column is equipped with a support rod 31, one end of which is fixedly connected to the lifting platform 2 by bolts, and the other end of which is fixedly connected to the middle of the column by bolts.

[0031] A limiting ring 6 is welded to the top of the mounting bracket 3. The limiting ring 6 is horizontally positioned and is composed of two semicircular rings joined together by bolts. One of the semicircular rings is welded to the mounting bracket 3. Guide wheels 61 are installed on the inner wall of the limiting ring 6. At least three guide wheels 61 are provided, and all guide wheels 61 are evenly distributed at equal angles around the axis of the limiting ring 6. In this embodiment, three guide wheels 61 are provided, and all guide wheels 61 are evenly distributed at equal angles around the axis of the limiting ring 6. A rotating shaft 62 is installed inside the guide wheel 61. The axis of the rotating shaft 62 is vertical, and both ends of the rotating shaft 62 are welded to the inner wall of the limiting ring 6.

[0032] The specific usage process of this utility model is as follows: Before installing the aircraft main landing gear, the drive mechanism must be operated to lower the lifting platform 2 to its lowest position. Then, the mounting bracket 3, support rod 31, and limiting ring 6 are assembled. Next, the aircraft main landing gear is placed on the lifting platform 2, ensuring that the bottom of the main landing gear is in close contact with the buffer pad 51 on the rotating disk 5, while ensuring that the upper part of the main landing gear is inside the limiting ring 6. After completing the above operations, the chassis 1 is moved to the predetermined installation position. After reaching the predetermined position, the height of the lifting platform 2 is adjusted using the drive mechanism, while the rotating disk 5 is rotated to adjust the direction of the aircraft main landing gear, allowing it to smoothly enter the landing gear bay. Inside the landing gear bay, the height and direction of the aircraft main landing gear are fine-tuned until the installation of the aircraft main landing gear pivot is completed. After the pivot is installed, the height of the lifting platform 2 is lowered using the drive mechanism, and the mounting bracket 3, support rod 31, and limiting ring 6, which have completed their auxiliary support tasks, are removed. Then, the chassis 1 is moved again, and after the movement is completed, the drive mechanism is operated again to raise the lifting platform 2. At this point, the rotating platform 5 will pull the bottom of the aircraft's main landing gear upward, causing the main landing gear to tilt to facilitate subsequent installation procedures. After all installation work is completed, the height of the lifting platform 2 will be lowered again, and finally the chassis 1 will be removed, thus completing the installation process of the aircraft's main landing gear.

[0033] The disassembly process of the aircraft's main landing gear is the complete reverse of the installation process. First, the chassis 1 is moved to a suitable position under the aircraft's main landing gear, and the elevator 2 is raised so that the rotating disc 5 contacts and supports the bottom of the aircraft's main landing gear. Next, the direction of the aircraft's main landing gear is adjusted to a suitable angle, and the height of the elevator 2 is lowered until the aircraft's main landing gear is completely placed on the elevator 2. Then, the mounting bracket 3, support rod 31, and limiting ring 6 are installed to assist in securing the aircraft's main landing gear. Afterward, the elevator 2 is raised again, and the rotating disc 5 is rotated to adjust the direction of the aircraft's main landing gear, allowing it to be moved out of the landing gear bay. After removal, the height of the elevator 2 is lowered, the mounting bracket 3, support rod 31, and limiting ring 6 are removed, and finally, the chassis 1 is removed, completing the disassembly of the aircraft's main landing gear.

[0034] As can be seen from the above embodiments, the beneficial effects of this utility model are as follows: the rotating disk supports and supports the aircraft's main landing gear, while the limiting ring limits the main landing gear, ensuring it remains vertical. The hydraulic actuator, as a power source, drives the lifting platform via a chain, enabling height adjustment of the aircraft's main landing gear. The rotating disk itself allows for convenient and quick adjustment of the aircraft's main landing gear direction. The guide wheels on the inner wall of the limiting ring assist in the rotation of the main landing gear, reducing rotational resistance and making the rotation process smoother. In summary, this solution not only achieves precise height adjustment of the aircraft's main landing gear, but more importantly, it allows for easy and flexible adjustment of the aircraft's main landing gear direction without rotating the chassis, greatly improving operational convenience and maintenance efficiency, and bringing significant convenience to the maintenance of the aircraft's main landing gear.

[0035] The above description of the disclosed embodiments enables those skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A vehicle for disassembling and assembling aircraft main landing gear, comprising a chassis (1), characterized in that, A lifting platform (2) is provided on the chassis (1). A drive mechanism is also provided on the chassis (1). The drive mechanism can drive the lifting platform (2) to lift. A support plate (4) is fixed on the lifting platform (2). A rotating plate (5) is installed on the support plate (4). The rotating plate (5) is rotatably connected to the support plate (4). A mounting frame (3) is also fixed on the lifting platform (2). A limit ring (6) is fixed on the top of the mounting frame (3). A guide wheel (61) is installed on the inner wall of the limit ring (6).

2. Aircraft main landing gear dismounting cart according to claim 1, characterized in that A guide rod (13) is provided on the chassis (1). The bottom of the guide rod (13) is fixedly connected to the chassis (1). A handrail (12) is fixed to the top of the guide rod (13). A fixing block (14) is fixed to the middle of the guide rod (13).

3. Aircraft main landing gear dismounting cart according to claim 2, characterized in that The drive mechanism includes a hydraulic actuator (7), the cylinder of which is fixed on the chassis (1). A connecting shaft (71) is fixed to the end of the telescopic rod of the hydraulic actuator (7). Rollers (72) are rotatably connected to both ends of the connecting shaft (71). A chain (73) is wrapped around the top of the roller (72). One end of the chain (73) is fixedly connected to the fixed block (14), and the other end of the chain (73) is fixedly connected to the lifting platform (2).

4. Aircraft main landing gear dismounting cart according to claim 3, characterized in that The end of the telescopic rod of the hydraulic actuator (7) is fixedly connected to the middle of the connecting shaft (71), and the connecting shaft (71) is placed horizontally.

5. The aircraft main landing gear dolly of claim 2, wherein, A limit plate (22) is provided on the side of the lifting platform (2) near the handrail (12). Two limit blocks (23) are fixed on the limit plate (22). The two limit blocks (23) are located on both sides of the guide rod (13).

6. The aircraft main landing gear dolly of Claim 1, wherein, The lifting platform (2) is fixed with a mounting base (21), and the bottom of the mounting bracket (3) is inserted into the mounting base (21).

7. The aircraft main landing gear dolly of Claim 1, wherein, A support rod (31) is provided on the lifting platform (2). One end of the support rod (31) is fixedly connected to the lifting platform (2), and the other end of the support rod (31) is fixedly connected to the middle of the mounting frame (3).

8. The aircraft main landing gear dolly of Claim 1, wherein, The guide wheel (61) has a rotating shaft (62) installed inside. The axis of the rotating shaft (62) is vertical, and both ends of the rotating shaft (62) are fixedly connected to the inner wall of the limiting ring (6).

9. Aircraft main landing gear dolly according to claim 8, characterized in that There are at least three guide wheels (61), and all guide wheels (61) are evenly distributed at equal angles around the axis of the limiting ring (6).

10. The aircraft main landing gear dolly of Claim 1, wherein, A buffer pad (51) is fixed to the top of the rotating disk (5).

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