An aircraft wheel hub paint spraying device

Abstract

The application discloses an airplane wheel hub paint spraying device and relates to the technical field of airplane maintenance. The airplane wheel hub paint spraying device comprises a support assembly, a turnover assembly and a wheel hub mounting assembly. The support assembly comprises a base and a support frame, and the support frame is arranged on the base. The turnover assembly comprises a bearing seat, a turnover shaft, a support arm and a rotating rod. The bearing seat is installed on the support frame, the turnover shaft is horizontally arranged in the bearing seat, and the support arm is fixedly connected to the two ends of the turnover shaft. The rotating rod is arranged at the end of the support arm away from the turnover shaft, the rotating rod is in transmission connection with the support arm, and the axis of the rotating rod is perpendicular to the axial direction of the turnover shaft. The wheel hub mounting assembly is sleeved on the rotating rod and is fixedly connected with the rotating rod. The airplane wheel hub paint spraying device provided by the application improves the spraying efficiency and safety of the airplane wheel hub, improves the paint surface quality, reduces the material cost, and realizes the airplane wheel hub paint spraying operation of multiple models.

Description

Technical Field

[0001] This utility model relates to the field of aircraft maintenance technology, and in particular to an aircraft wheel hub painting device. Background Technology

[0002] In the field of aircraft maintenance, wheel hubs, as an important component of the landing gear system, have strict standards for their painting, corrosion protection, and decorative processes. Currently, the industry generally adopts the following traditional technical solutions for painting civil aircraft wheel hubs: First, the wheel hub to be painted is placed directly on a simple flatbed cart, wooden pallet, or simple roller frame on the ground using simple supports or flatbed carts; then, manual segmented painting and flipping are performed. Operators first paint the visible surfaces of the wheel hub (such as the outer side and some spokes), and after the paint reaches a surface dry state, the wheel hub is manually flipped to paint the other side (inner side or back). Disposable material masking methods are used, employing masking tape, special protective stickers, or plastic plugs to individually stick or seal bolt holes, valve holes, bearing housing holes, and sidewall grooves on the wheel hub, etc., areas that do not need to be painted. Current aircraft wheel hub operations are inefficient and rely heavily on manual experience. Existing processes typically involve placing the wheel hub directly on a flatbed cart or the ground for painting. Operators must complete the spraying on one side and wait for the paint to surface dry before manually flipping the wheel hub to work on the other side. The spraying cycle for a single wheel hub can take more than 4 hours, and the manual flipping process poses risks of bumps, damage, and safety hazards. Secondly, paint quality is difficult to guarantee, resulting in a high rework rate. The contact surface between the wheel hub and the flatbed truck or ground cannot be covered during spraying, leading to discontinuous paint film. After drying, defects such as paint sticking, runs, and indentations easily occur on the contact surface, affecting appearance quality and coating adhesion. The current process has a yield rate of only about 60%, resulting in frequent rework and significant material and labor losses.

[0003] Therefore, there is an urgent need for a new type of aircraft wheel hub painting device to overcome the problems of low construction efficiency, difficulty in guaranteeing paint quality, high rework rate, and inability to effectively paint the wheel hub in one go when using existing technology. Utility Model Content

[0004] In view of this, this application provides an aircraft wheel hub painting device, the main purpose of which is to solve the problems of low construction efficiency, difficulty in guaranteeing paint quality, high rework rate and inability to effectively paint the wheel hub in one go when painting wheel hubs in the prior art.

[0005] To solve the above problems, this utility model provides the following technical solution: An aircraft wheel hub painting device, comprising: A support assembly includes a base and a support frame, the support frame being disposed on the base; The flipping assembly includes a bearing housing, a flipping shaft, a support arm, and a rotating rod. The bearing housing is mounted on the support frame, the flipping shaft is horizontally inserted into the bearing housing, and the support arm is fixedly connected to both ends of the flipping shaft. The rotating rod is located at the end of the support arm away from the flipping shaft, the rotating rod is kinetically connected to the support arm, and the axis of the rotating rod is perpendicular to the axis of the flipping shaft. A hub mounting assembly is sleeved on the rotating rod and fixedly connected to the rotating rod.

[0006] Specifically, the wheel hub mounting assembly is a modular wheel hub adapter, which is detachably connected to the end of the support arm.

[0007] Specifically, the wheel hub mounting assembly includes a connecting part and a clamping part. The connecting part is fixedly connected to the rotating rod, the clamping part is used to clamp the aircraft wheel hub, and the connecting part is threadedly connected to the wheel hub clamping part.

[0008] Specifically, the clamping part has a positioning stop and a plurality of bolt clearance holes on the end face away from the free end of the rotating rod. The positioning stop is used to fit with the inner ring of the aircraft wheel hub, and the bolt clearance holes are used to be coaxially aligned with the bolts of the aircraft wheel hub.

[0009] Specifically, each end of the flipping shaft is fixedly connected to two support arms, and the two support arms are arranged symmetrically about the axis of the flipping shaft.

[0010] Specifically, the flipping assembly also includes a linkage bushing and a fastener. The linkage bushing is fixedly sleeved on the flipping shaft and rotates in cooperation with the bearing seat. The fastener clamps and fixes the support arm to the shaft end of the flipping shaft.

[0011] Specifically, it also includes a flipping drive component and an angle positioning component. The flipping drive component is mounted on the support frame and is connected to the flipping shaft to drive the flipping shaft to rotate. The angle positioning component is used to lock the rotating rod at a predetermined flipping angle position.

[0012] Specifically, it also includes a protective component, which includes a protective cover and a protective plug. The protective cover is used to cover the outside of the aircraft wheel hub, and the protective plug is used to be embedded in the central hole of the aircraft wheel hub, and together with the protective cover, they enclose and form a protective chamber for the aircraft wheel hub.

[0013] Specifically, the protective plug is a bolt protective plug, which includes a flange and a cylindrical section. The cylindrical section is coaxially disposed in the middle of the flange, and the diameter of the flange is larger than the diameter of the cylindrical section.

[0014] Specifically, the base is equipped with casters, and the casters are equipped with a brake locking structure.

[0015] Therefore, the aircraft wheel hub painting device of this utility model, through integrated flipping components and rotating rods, achieves full-angle, multi-directional positional conversion of the wheel hub during the painting process, reducing manual flipping. The painting cycle for a single wheel hub can be reduced from over 14 hours to less than 7 hours, eliminating safety hazards. Secondly, it improves paint quality. The wheel hub has no fixed contact points throughout the painting process, and combined with full-angle rotation, continuous one-time painting can be achieved, avoiding defects such as paint adhesion, paint runs, and indentations on the contact surface, increasing the yield rate to over 95%. Simultaneously, it reduces consumable costs and protection time. A reusable metal protective plug assembly is designed to replace disposable tape and stickers, achieving quick and precise sealing of bolt holes and wheel hub sidewalls. This reduces protection operation time and material consumption, with the protection cost for a single wheel hub expected to decrease by over 70%. Furthermore, it shortens the replacement time for wheel hubs of various aircraft models. Through modularly designed wheel hub adapter components, adapter modules can be replaced for different aircraft models, achieving precise positioning and clamping.

[0016] Therefore, the disadvantages described at the beginning were avoided and the corresponding advantages were obtained. Attached Figure Description

[0017] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of this application. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings: Figure 1 This paper shows a schematic diagram of the structure of an aircraft wheel hub painting device provided in an embodiment of this application; Figure 2 This illustration shows a schematic diagram of the structure of an aircraft wheel hub painting device connected to an aircraft wheel hub according to an embodiment of this application. Figure 3 A schematic diagram of the wheel hub mounting assembly provided in an embodiment of this application is shown; Figure 4 A schematic diagram of the structure of the protection component provided in an embodiment of this application is shown; Figure 5 A schematic diagram of the structure of the protective plug provided in an embodiment of this application is shown.

[0018] Figure label: 1-Bracket assembly, 11-Base, 12-Support frame; 2-Flipping assembly, 21-Bearing seat, 22-Flipping shaft, 23-Support arm, 24-Rotating rod, 25-Linkage bushing, 26-Fastener; 3-Hub mounting assembly, 31-Connecting part, 32-Clamping part; 4-Aircraft hub; 5-Protective assembly, 51-First protective cover, 52-Second protective cover, 53-Protective plug. Detailed Implementation

[0019] The following detailed embodiments are provided to help the reader gain a full understanding of the methods, apparatus, and / or systems described herein. However, various changes, modifications, and equivalents of the methods, apparatus, and / or systems described herein will be apparent after understanding the disclosure of this application. For example, the order of operations described herein is merely illustrative and is not limited to the order set forth herein; rather, changes that will be apparent after understanding the disclosure of this application may be made, except for operations that must occur in a specific order. Furthermore, for clarity and brevity, descriptions of features known in the art may be omitted.

[0020] The features described herein may be implemented in different forms and should not be construed as being limited to the examples described herein. Rather, the examples described herein have been provided merely to illustrate some of the many feasible ways of implementing the methods, apparatus, and / or systems described herein that will be apparent upon understanding the disclosure of this application.

[0021] Throughout the specification, when an element (such as a layer, region, or substrate) is described as being "on" another element, "connected to" another element, "bonded to" another element, "on" another element, or "covering" another element, it may be directly "on" another element, "connected to" another element, "bonded to" another element, "on" another element, or "covering" another element, or there may be one or more other elements in between. In contrast, when an element is described as being "directly on" another element, "directly connected to" another element, "directly bonded to" another element, "directly on" another element, or "directly covering" another element, there may be no other elements in between.

[0022] As used herein, the term “and / or” includes any one of the relevant items listed and any combination of any two or more items.

[0023] Although terms such as “first,” “second,” and “third” may be used herein to describe individual components, assemblies, regions, layers, or parts, these components, assemblies, regions, layers, or parts are not limited by these terms. Rather, these terms are used only to distinguish one component, assembly, region, layer, or part from another. Therefore, without departing from the teachings of the examples described herein, the first component, assembly, region, layer, or part referred to as the second component, assembly, region, layer, or part may also be referred to as the second component, assembly, region, layer, or part.

[0024] For ease of description, spatial relation terms such as “above,” “upper,” “below,” and “lower” are used herein to describe the relationship between one element and another, as shown in the accompanying drawings. Such spatial relation terms are intended to include not only the orientation depicted in the drawings but also different orientations of the device during use or operation. For example, if the device in the drawings is flipped, an element described as being “above” or “upper” relative to another element will subsequently be “below” or “lower” relative to that other element. Therefore, the term “above” includes both “above” and “below” orientations depending on the spatial orientation of the device. The device may also be positioned in other ways (e.g., rotated 90 degrees or in other orientations), and the spatial relation terms used herein will be interpreted accordingly.

[0025] The terminology used herein is for the purpose of describing various examples only and is not intended to limit this disclosure. Unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. The terms “comprising,” “including,” and “having” enumerate the stated features, quantities, operations, components, elements, and / or combinations thereof, but do not exclude the presence or addition of one or more other features, quantities, operations, components, elements, and / or combinations thereof.

[0026] Variations in the shapes shown in the accompanying drawings may occur due to manufacturing techniques and / or tolerances. Therefore, the examples described herein are not limited to the specific shapes shown in the accompanying drawings, but include changes in shape that may occur during manufacturing.

[0027] The features of the examples described herein can be combined in various ways that will be apparent upon understanding the disclosure of this application. Furthermore, although the examples described herein have a wide variety of constructions, other constructions are possible, as will be apparent upon understanding the disclosure of this application.

[0028] In the field of aircraft maintenance, aircraft wheel hubs, as an important component of the landing gear system, have strict technical standards for their painting, corrosion protection, and decoration processes. Currently, the industry commonly uses simple support or flatbed cart methods, placing the wheel hubs to be painted directly on ordinary flatbed carts, wooden pallets, or simple roller racks on the ground. Operators first spray the visible surfaces of the wheel hub, and after the paint is surface dry, they manually flip the wheel hub to work on the other side. At the same time, masking tape, special protective stickers, or plastic plugs are used to cover or seal areas that do not need to be painted, such as bolt holes. The above-mentioned construction methods have low efficiency, with the painting cycle for a single wheel hub reaching more than 14 hours. The manual turning process is prone to bumps and damage, and poses safety hazards. The contact surface between the wheel hub and the flatbed or ground cannot be covered during the painting process, resulting in discontinuous paint film. After drying, defects such as paint sticking, paint running, and indentations are likely to occur, and the pass rate of wheel hub painting is about 60%. The protective process is cumbersome, requiring a large amount of disposable materials for manual masking, which is costly and inconsistent. In addition, airlines usually include multiple aircraft models with large differences in wheel hub size and structure. The existing simple support method is difficult to shorten the changeover time and accurately position the hubs. Improving the versatility of the tooling facilitates the production of wheel hubs for different aircraft models.

[0029] Therefore, this application provides an aircraft wheel hub painting device, such as... Figure 1 and Figure 2 As shown, it includes: a bracket assembly 1, including a base 11 and a support frame 12, with the support frame 12 mounted on the base 11; a flipping assembly 2, including a bearing seat 21, a flipping shaft 22, a support arm 23, and a rotating rod 24, with the bearing seat 21 mounted on the support frame 12, the flipping shaft 22 horizontally passing through the bearing seat 21, and the support arm 23 fixedly connected to both ends of the flipping shaft 22; the rotating rod 24 is located at the end of the support arm 23 away from the flipping shaft 22, and the rotating rod 24 is drively connected to the support arm 23, with the axis of the rotating rod 24 perpendicular to the axis of the flipping shaft 22; and a hub mounting assembly 3, which is sleeved on the rotating rod 24 and fixedly connected to the rotating rod 24.

[0030] Specifically, an aircraft wheel hub painting device according to an embodiment of this application includes a bracket assembly 1, a flipping assembly 2, and a wheel hub mounting assembly 3. The bracket assembly 1 includes a base 11 and a support frame 12. There are two sets of support frames 12, and the two sets of support frames 12 are respectively fixed to the upper surface of the base 11. The support frame 12 is used to install the flipping assembly 2 to improve the stability of the device during the flipping process and reduce the problem of uneven spraying caused by shaking.

[0031] The flipping assembly 2 includes a bearing housing 21, a flipping shaft 22, a support arm 23, and a rotating rod 24. The bearing housing 21 is mounted on the central crossbeam of the support frame 12, and the flipping shaft 22 is horizontally inserted into the bearing housing 21 and rotatably engaged with it. In this embodiment, two flipping shafts 22 are preferably present, with a support arm 23 fixedly connected to each end of each flipping shaft 22, and the two support arms 23 are symmetrically arranged with respect to the axis of the flipping shaft 22. The rotating rod 24 is drive-connected to the support arm 23, and the axis of the rotating rod 24 is perpendicular to the axis of the flipping shaft 22.

[0032] The hub mounting assembly 3 is sleeved on the rotating rod 24 and fixedly connected to the rotating rod 24. Preferably, there are four sets of hub mounting assemblies 3 and rotating rods 24, so that the device can support four aircraft hubs 4 at the same time. When one station is in the painting state, the operator can perform loading and unloading operations at other stations to achieve continuous operation and reduce the waiting time for loading and unloading.

[0033] In this embodiment, as Figure 3 As shown, the wheel hub mounting assembly 3 is a modular wheel hub adapter, which is detachably connected to the end of the support arm 23.

[0034] Specifically, the wheel hub mounting assembly 3 is fitted onto the rotating rod 24 and is fixedly connected to the rotating rod 24. The wheel hub mounting assembly 3 is a modular wheel hub adapter and is detachably connected to the end of the rotating rod 24.

[0035] In this embodiment, the wheel hub mounting assembly 3 includes a connecting part 31 and a clamping part 32. The connecting part 31 is fixedly connected to the rotating rod 24, and the clamping part 32 is used to clamp the aircraft wheel hub 4. The connecting part 31 is threadedly connected to the wheel hub clamping part 32.

[0036] Specifically, the wheel hub mounting assembly 3 includes a connecting part 31 and a clamping part 32. The connecting part 31 is fixedly connected to the rotating rod 24, and the clamping part 32 is used to clamp the aircraft wheel hub 4. The connecting part 31 and the clamping part 32 are threadedly connected. The modular design of the wheel hub mounting assembly 3 allows for the replacement of adapter modules for different aircraft models, achieving precise positioning and clamping. It can adapt to different aircraft models, and the replacement of the modular clamping part shortens the changeover time, solving the problem of insufficient multi-aircraft compatibility in existing systems.

[0037] In this embodiment, the end face of the clamping part 32 away from the free end of the rotating rod 24 is provided with a positioning stop and a plurality of bolt clearance holes. The positioning stop is used to fit with the inner ring of the aircraft hub 4, and the bolt clearance holes are used to be coaxially aligned with the bolts of the aircraft hub 4.

[0038] Specifically, the clamping part 32 has a positioning stop and multiple bolt clearance holes on its end face away from the free end of the rotating rod 24. The positioning stop is used to fit against the inner ring of the aircraft hub 4 to achieve radial positioning, and the bolt clearance holes are used to align with the bolts of the aircraft hub 4 coaxially. The above positioning structure helps to ensure the coaxiality and repeatability of the hub installation, and reduces the problem of uneven paint film thickness caused by hub misalignment during the painting process.

[0039] In this embodiment, each end of the flip shaft 22 is fixedly connected to two support arms 23, and the two support arms 23 are arranged symmetrically about the axis of the flip shaft 22.

[0040] In this embodiment, the flipping assembly 2 also includes a linkage bushing 25 and a fastener 26. The linkage bushing 25 is fixedly sleeved on the flipping shaft 22 and rotates in cooperation with the bearing seat 21. The fastener 26 clamps and fixes the support arm 23 to the shaft end of the flipping shaft 22.

[0041] Specifically, the flipping assembly 2 also includes a linkage sleeve 25 and a fastener 26. The linkage sleeve 25 is fixedly sleeved on the flipping shaft 22 and rotatably engages with the bearing seat 21. The fastener 26 clamps and fixes the support arm 23 to the shaft end of the flipping shaft 22, so that the support arm 23 flips synchronously with the flipping shaft 22. The above-mentioned linkage structure facilitates the smooth transmission of the flipping motion, reduces the loosening or displacement of the support arm 23 during the flipping process, and improves the spraying accuracy.

[0042] In this embodiment, a flipping drive and an angle positioning component are also included. The flipping drive is mounted on the support frame 12 and is connected to the flipping shaft 22 for driving the flipping shaft 22 to rotate. The angle positioning component is used to lock the rotating rod 24 at a predetermined flipping angle position.

[0043] Specifically, the flipping assembly 2 also includes a flipping drive and an angle positioning component. The flipping drive is mounted on the support frame 12 and is connected to the flipping shaft 22 for transmission, driving the flipping shaft 22 to flip 180° or 360° around the horizontal axis. The angle positioning component is used to lock the rotating rod 24 at a predetermined flipping angle position. The angle positioning component can be a combination of an indexing plate and a pin lock. The indexing plate is fixed on the flipping shaft 22, and the pin lock is mounted on the support frame 12. The pin of the pin lock can be inserted into the positioning hole of the indexing plate to lock the angle position of the flipping shaft 22. Through the cooperation of the flipping drive and the angle positioning component, precise angle control and stable locking of the hub can be achieved, allowing the operator to pause at any angle and perform precise spraying.

[0044] In this embodiment, as Figure 4 and Figure 5 As shown, it also includes a protective component 5, which includes a protective cover and a protective plug 53. The protective cover is used to cover the outside of the aircraft hub 4, and the protective plug 53 is used to be embedded in the central hole of the aircraft hub 4, and together with the protective cover, they enclose and form a protective chamber of the aircraft hub 4.

[0045] Specifically, the protective component 5 includes a protective cover and a protective plug 53. The protective cover is used to cover the outside of the aircraft wheel hub 4. The protective cover includes a first protective cover 51 and a second protective cover 52. The second protective cover 52 is an open hemispherical or bowl-shaped structure. The open end of the protective cover has a flange, and the inner wall of the protective cover has multiple positioning blocks. In use, the protective cover is fastened to the center hole of the aircraft wheel hub 4, and the positioning blocks abut against the inner wall of the center hole of the aircraft wheel hub 4 to fix the protective cover. The protective component 5 is used to seal non-painted areas to maintain the neatness of the coating boundary and the cleanliness of precision parts.

[0046] In this embodiment, the protective plug 53 is a bolt protective plug, which includes a flange and a cylindrical section. The cylindrical section is coaxially disposed in the middle of the flange, and the diameter of the flange is larger than the diameter of the cylindrical section.

[0047] Specifically, the protective plug 53 is a bolt protection plug, comprising a flange and a cylindrical section. The cylindrical section is coaxially positioned in the center of the flange, and the diameter of the flange is larger than the diameter of the cylindrical section. The outer circumferential surface of the cylindrical section has a snap-fit ​​flange, which is used to engage with the inner wall of the bolt hole in the aircraft wheel hub 4 to prevent detachment. The end face of the flange facing the aircraft wheel hub 4 is used to fit against the wheel hub end face around the bolt hole, preventing paint from entering the bolt hole. The protective plug 53 is a metal component, such as aluminum alloy or stainless steel, and is reusable. The protective plug 53 can be designed as conical or stepped, with a magnetic snap-fit ​​structure at the base for insertion or snapping into bolt holes, valve stem holes, and other parts of the wheel hub. The reusable metal protective plug replaces disposable tape and stickers, reducing protection operation time and material consumption. The protection cost per wheel hub is expected to be reduced by more than 70%, reducing the problem of inconsistent application of masking materials.

[0048] In this embodiment, the base 11 is equipped with casters, and the casters are equipped with a brake locking structure.

[0049] Specifically, the bottom of the base 11 is equipped with casters, which have a brake locking structure to facilitate the overall movement of the device and the fixing of the work position.

[0050] Working Principle: Step 1, Installation and Adjustment: Based on the aircraft hub model to be painted, select the corresponding modular clamping part 32. Install the clamping part 32 onto the rotating rod 24 via the connecting part 31. Fit the aircraft hub 4 onto the clamping part 32, ensuring the inner ring of the aircraft hub 4 fits against the positioning stop, achieving clamping and positioning. By changing the modular adapter parts, it can adapt to the replacement of hubs of different aircraft models, with a single set replacement time controlled within a few minutes. Step 2, Protective Installation: The operator installs the corresponding specification protective plug 53 into all bolt holes of the aircraft hub 4, and fastens the protective cover to the center hole of the aircraft hub 4, so that the positioning stop abuts against the inner wall of the center hole, achieving sealing of bolt holes, bearing holes, side walls, and other parts that need protection. This step, through the removal and installation of metal protective plugs, shortens the protection process from tens of minutes to a few minutes, and the sealing effect is better than manual pasting. Step 3, Full-Angle Spraying: Start the device. First, the aircraft hub 4 is adjusted to a starting position suitable for spraying using the flip drive. The spray gun is aimed at the aircraft hub 4, and the rotating rod 24 drives the aircraft hub 4 to rotate at a constant speed. The operator or automatic spray gun sweeps along the axial direction of the aircraft hub 4 to complete the spraying of the first area. Subsequently, the aircraft hub 4 is driven to rotate 90° or 180° around the horizontal axis by the flip drive, and the angle positioning component locks the flip axis 22 at this angle position. The process is then switched to the next surface to be sprayed, and the rotation and spraying actions are repeated until all outer surfaces are sprayed. Using this non-grounded, contactless clamping method, the hub has no fixed contact points throughout the spraying process. Combined with full-angle rotation and flipping, continuous spraying can be achieved in one go, which can reduce defects such as paint adhesion, paint runs, and indentations on the contact surface, thus reducing paint defects and improving the product qualification rate. Step 4, Drying and Unloading: After spraying, the aircraft hub 4 can continue to be rotated and flipped on the device for leveling and surface drying. After the paint surface reaches a surface dry state, remove the protective cover and protective plug 53. The protective plug 53 can be reused immediately. Loosen the clamping part 32 and remove the painted aircraft wheel hub 4, thus realizing continuous painting operation.

[0051] The aircraft wheel hub painting device provided in this embodiment, through the cooperation of the bracket assembly 1, the flipping assembly 2, and the wheel hub mounting assembly 3, enables non-grounded, contactless support and omnidirectional painting conversion of aircraft wheel hubs. Compared with existing technologies, it improves painting efficiency and safety, enhances paint quality, reduces consumable costs, and is suitable for wheel hub painting operations of different aircraft models.

[0052] The scope of protection of this utility model is not limited to the above-described embodiments. Obviously, those skilled in the art can make various modifications and variations to this utility model without departing from the scope and spirit of this application. If these modifications and variations fall within the scope of this utility model and its equivalents, then the intent of this utility model also includes these modifications and variations.

Claims

1. An aircraft wheel hub painting device, characterized in that, include: A support assembly includes a base and a support frame, the support frame being disposed on the base; The flipping assembly includes a bearing housing, a flipping shaft, a support arm, and a rotating rod. The bearing housing is mounted on the support frame, the flipping shaft is horizontally inserted into the bearing housing, and the support arm is fixedly connected to both ends of the flipping shaft. The rotating rod is located at the end of the support arm away from the flipping shaft, the rotating rod is kinetically connected to the support arm, and the axis of the rotating rod is perpendicular to the axis of the flipping shaft. A hub mounting assembly is sleeved on the rotating rod and fixedly connected to the rotating rod.

2. The aircraft wheel hub painting device according to claim 1, characterized in that, The wheel hub mounting assembly is a modular wheel hub adapter, which is detachably connected to the end of the support arm.

3. The aircraft wheel hub painting device according to claim 2, characterized in that, The wheel hub mounting assembly includes a connecting part and a clamping part. The connecting part is fixedly connected to the rotating rod, and the clamping part is used to clamp the aircraft wheel hub. The connecting part is threadedly connected to the wheel hub clamping part.

4. The aircraft wheel hub painting device according to claim 3, characterized in that, The clamping part has a positioning stop and a plurality of bolt clearance holes on its end face away from the free end of the rotating rod. The positioning stop is used to fit with the inner ring of the aircraft wheel hub, and the bolt clearance holes are used to be coaxially aligned with the bolts of the aircraft wheel hub.

5. The aircraft wheel hub painting device according to claim 1, characterized in that, Two support arms are fixedly connected to each end of the flipping shaft, and the two support arms are arranged symmetrically about the axis of the flipping shaft.

6. The aircraft wheel hub painting device according to claim 1, characterized in that, The flipping assembly also includes a linkage bushing and fasteners. The linkage bushing is fixedly sleeved on the flipping shaft and rotates in cooperation with the bearing seat. The fasteners clamp and fix the support arm to the shaft end of the flipping shaft.

7. The aircraft wheel hub painting device according to claim 1, characterized in that, It also includes a flipping drive and an angle positioning component. The flipping drive is mounted on the support frame and is connected to the flipping shaft to drive the flipping shaft to rotate. The angle positioning component is electrically connected to the flipping drive and is used to lock the rotating rod at a predetermined flipping angle position.

8. The aircraft wheel hub painting device according to claim 1, characterized in that, It also includes a protective component, which includes a protective cover and a protective plug. The protective cover is used to cover the outside of the aircraft wheel hub, and the protective plug is used to be embedded in the center hole of the aircraft wheel hub, and together with the protective cover, they enclose a protective chamber of the aircraft wheel hub.

9. The aircraft wheel hub painting device according to claim 8, characterized in that, The protective plug is a bolt protective plug, which includes a flange and a cylindrical section. The cylindrical section is coaxially disposed in the middle of the flange, and the diameter of the flange is larger than the diameter of the cylindrical section.

10. The aircraft wheel hub painting device according to claim 1, characterized in that, The base is equipped with casters, and the casters are equipped with a brake locking mechanism.

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