Airplane wheel hub structure and mounting method thereof

Abstract

The invention discloses an airplane wheel hub structure and a mounting method thereof, and relates to the field of hubs, the airplane wheel hub structure comprises a hub connecting part, spokes and a rim, the rim is connected with the hub connecting part through the spokes, the spokes are provided with air channel grooves, the tail ends of the air channel grooves are communicated with heat dissipation channels, the tail ends of the heat dissipation channels are located at the rim, and the heat dissipation channels are communicated with the air channel grooves. The outer side of the air channel groove is connected with an air flow leading-in assembly used for leading air flow into the air channel groove. The air channel grooves formed in the spokes are matched with the annular protrusions, so that air flow can be driven to flow into the heat dissipation channels along the air channel grooves, then heat dissipation is conducted on a tire on the outer side of the rim, and safety accidents caused by overheat deformation of the tire are avoided. And meanwhile, the hub can be more conveniently mounted in cooperation with the mounting equipment disclosed by the invention, the driving assembly can adjust the distance of the hub relative to the mounting position, the telescopic rod controls the height of the hub, and meanwhile, the manual mounting difficulty is greatly reduced in cooperation with the mounting auxiliary assembly and the mechanical arm.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of wheel hubs, in particular to an aircraft wheel hub structure and a mounting method thereof. BACKGROUND

[0002] During the operation of an aircraft, the wheel hub and tire need to withstand a large load and friction, which easily generates a large amount of heat. In the existing design of the aircraft wheel hub structure, there is a lack of effective airflow guiding and heat dissipation mechanism, which cannot introduce and act on the tire outside the rim with airflow in a targeted manner, resulting in deformation of the tire due to overheating, which not only affects the service life of the tire, but also may cause safety accidents, threatening the safety of the aircraft operation.

[0003] At the same time, the current installation process of the aircraft wheel hub relies on traditional equipment and a large amount of manual operation. The existing installation equipment lacks flexible distance adjustment and height control functions, making it difficult to accurately adjust the attitude of the wheel hub relative to the installation position; and lacks efficient installation auxiliary components and mechanical arm cooperative matching, resulting in a large difficulty and complicated operation of manual installation, which not only increases the labor cost, but also easily affects the installation precision and efficiency due to operation errors, and cannot meet the demand for rapid and accurate installation of the wheel hub in aircraft maintenance and repair. SUMMARY

[0004] The purpose of the present application is to provide an aircraft wheel hub structure and a mounting method thereof to solve the problems raised in the background.

[0005] To achieve the above purpose, the present application provides the following technical solutions: An aircraft wheel hub structure, comprising a hub connecting portion, a spoke and a rim, the rim being connected with the hub connecting portion through the spoke, a gas channel is formed on the spoke, and a heat dissipation channel is arranged at the end of the gas channel, the end of the heat dissipation channel being located at the rim, and a gas flow introduction assembly is connected outside the gas channel to introduce gas flow into the gas channel.

[0006] As a further scheme of the present application, each of the spokes is in a Y-shaped structure, and the heat dissipation channel is arranged in the Y-shaped structure of the spoke, and the heat dissipation channel is in communication with the gas channel.

[0007] As a further scheme of the present application, the gas flow introduction assembly comprises a sealing plate, a ring-shaped protrusion is fixedly connected outside the sealing plate, the ring-shaped protrusion is in communication with the gas channel, and after the sealing plate is connected outside the gas channel, the gas channel is only in communication with the heat dissipation channel and the ring-shaped protrusion.

[0008] The application discloses an installation method of an aircraft wheel hub, and the method is installed by using equipment, the equipment comprises a moving base, an adjusting base is fixedly connected to the moving base, a sliding base is slidably connected to the adjusting base, a driving assembly for driving the sliding base to move is arranged on the side of the adjusting base, an extension rod is fixedly connected above the sliding base, an installation auxiliary assembly is fixedly connected to the top of the extension rod, and the wheel hub is installed through the installation auxiliary assembly.

[0009] As a further scheme of the application, two mechanical arms are fixedly connected above the moving base, moving wheels are fixedly connected below the moving base, and a handle is fixedly connected to the side of the moving base.

[0010] As a further scheme of the application, the driving assembly comprises a screw rod which is threadedly connected with the adjusting base, a sliding groove which is consistent with the axial direction of the screw rod is formed in the adjusting base, a driving piece is fixedly connected to the bottom of the sliding base, the driving piece is threadedly connected with the screw rod, the driving piece is slidably connected with the sliding groove, and the end of the screw rod is rotationally driven by a power unit.

[0011] As a further scheme of the application, the screw rod is provided with two screw rods which are arranged on the two sides of the adjusting base respectively, and a driven gear is connected to the end of each screw rod, the power unit comprises a driving motor which is fixedly connected to the moving base, a driving gear is fixedly connected to the output shaft of the driving motor, and the driving gear is engaged with the driven gear.

[0012] As a further scheme of the application, the driving motor is a double-output-shaft motor, a driving gear is fixedly connected to each output end of the driving motor, and the two driven gears are engaged with different driving gears respectively.

[0013] As a further scheme of the application, the installation auxiliary assembly comprises a vertical plate which is fixedly connected to the top of the extension rod, a clamping motor is fixedly connected to the vertical plate, a clamping plate is fixedly connected to the output shaft of the clamping motor, a plurality of arc-shaped grooves which are rotationally symmetrically distributed are formed in the clamping plate, the distance between each arc-shaped groove and the output shaft of the clamping motor is different, guide grooves which are equally angularly distributed are formed in the vertical plate, the number of the guide grooves is consistent with that of the arc-shaped grooves, a clamping rod is slidably connected in each guide groove, and the clamping rod is located in the corresponding arc-shaped groove.

[0014] As a further scheme of the application, the clamping motor is provided with two groups, and the wheel hub is fixed to the side of the vertical plate through the clamping rod.

[0015] Compared with the prior art, the present application has the beneficial effects that: the present application has simple structure, the air flow is guided to flow into the heat dissipation channel along the air channel groove through the air channel groove and the annular protrusion, and then the tire on the outer side of the rim is cooled, so that the safety accidents caused by the deformation of the tire due to overheating are avoided. Meanwhile, the installation equipment disclosed in the present application can be more convenient for hub installation, the driving assembly can adjust the distance of the hub relative to the installation position, the telescopic rod controls the height of the hub, and the installation auxiliary assembly and the mechanical arm greatly reduce the difficulty of manual installation. BRIEF DESCRIPTION OF DRAWINGS

[0016] Figure 1 It is a structural schematic view of an aircraft wheel hub structure.

[0017] Figure 2 It is a partial enlarged structural schematic view of an aircraft wheel hub structure.

[0018] Figure 3 It is a structural schematic view of a sealing plate in an aircraft wheel hub structure.

[0019] Figure 4 It is a structural schematic view of the installation equipment of the present application.

[0020] Figure 5 It is Figure 4 It is a partial enlarged structural schematic view of the position A in the above figure.

[0021] Figure 6 It is Figure 4 It is a structural schematic view from another perspective.

[0022] Figure 7 It is a structural schematic view of the sliding groove position in the installation equipment of the present application.

[0023] Figure 8 It is a partial transmission structural schematic view of the driving assembly in the installation equipment of the present application.

[0024] In the figure: 1, hub connecting part; 2, spoke; 3, rim; 4, air channel groove; 5, heat dissipation channel; 6, air flow introduction assembly; 7, sealing plate; 8, annular protrusion; 9, moving base; 10, adjusting seat; 11, sliding bottom plate; 12, driving assembly; 13, telescopic rod; 14, installation auxiliary assembly; 15, mechanical arm; 16, moving wheel; 17, handle; 18, screw rod; 19, sliding groove; 20, driving piece; 21, driven gear; 22, driving motor; 23, driving gear; 24, vertical plate; 25, clamping motor; 26, clamping plate; 27, arc-shaped groove; 28, guide groove; 29, clamping rod. DETAILED DESCRIPTION

[0025] It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict.

[0026] In the description of the present application, it needs to be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present application and simplifying the description, and does not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application. In addition, the terms "first", "second" and the like are only for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined with "first", "second" and the like can explicitly or implicitly include one or more features. In the description of the present application, unless otherwise stated, the meaning of "a plurality of" is two or more.

[0027] In the description of the present application, it needs to be understood that unless otherwise explicitly specified and limited, the terms "mounting", "connection", "connection" should be understood broadly, for example, it can be fixed connection, or detachable connection, or integral connection; it can be mechanical connection, or electrical connection; it can be directly connected, or indirectly connected through intermediate medium, or the communication inside two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood through specific circumstances.

[0028] The present application will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0029] Please refer to Figure 1 , Figure 2 and Figure 3 , an aircraft wheel hub structure, comprising a hub connecting part 1, a spoke 2 and a rim 3, the rim 3 is connected with the hub connecting part 1 through the spoke 2, a gas channel groove 4 is provided on the spoke 2, the gas channel groove 4 is provided with a heat dissipation channel 5 at the end, the heat dissipation channel 5 is located at the rim 3 at the end, and a gas flow introduction assembly 6 is connected outside the gas channel groove 4 to introduce gas flow into the gas channel groove 4.

[0030] The core of the aircraft wheel hub structure is to introduce gas flow into the gas channel groove 4 through the gas flow introduction assembly 6, and then through the gas channel groove 4 and the heat dissipation channel 5 to form a flow guide path, so as to accurately deliver the gas flow to the heat core area, and finally realize efficient heat dissipation and ensure the stability of the wheel operation.

[0031] Each spoke 2 has a Y-shaped structure, and each Y-shaped structure of the spoke 2 is provided with a heat dissipation channel 5, which is connected to the air passage 4. The airflow introduction component 6 includes a sealing plate 7, and an annular protrusion 8 is fixedly connected to the outside of the sealing plate 7. The annular protrusion 8 is connected to the air passage 4. After the sealing plate 7 is connected to the outside of the air passage 4, the air passage 4 is only connected to the heat dissipation channel 5 and the annular protrusion 8.

[0032] When the aircraft generates relative airflow during taxiing or takeoff and landing, the annular protrusion 8 in the airflow inlet assembly 6, due to its raised outer surface, has a higher airflow velocity on its outer side. Because of the high velocity and low air pressure, the airflow passes through the center of the annular protrusion 8 and enters the air duct groove 4. Within the air duct groove 4, the airflow flows along a predetermined path, and upon reaching the spoke 2, it splits into different heat dissipation channels 5 on the spoke 2. When the airflow exits from the end of the heat dissipation channel 5 to the rim 3, it quickly carries away the large amount of heat generated by the rim 3 during braking, reducing its temperature and preventing performance degradation or structural damage to the wheels due to high temperatures, ultimately completing a full active cooling cycle.

[0033] Please see Figure 4 and Figure 6 An installation method for an aircraft wheel hub structure is disclosed. The method employs the following equipment: a movable base 9, an adjusting seat 10 fixedly connected to the movable base 9, a sliding base plate 11 slidably connected to the adjusting seat 10, a driving assembly 12 for moving the sliding base plate 11 on the side of the adjusting seat 10, a telescopic rod 13 fixedly connected above the sliding base plate 11, and an installation auxiliary assembly 14 fixedly connected to the top of the telescopic rod 13. The wheel hub is installed via the installation auxiliary assembly 14. Two robotic arms 15 are fixedly connected above the movable base 9, movable wheels 16 are fixedly connected below the movable base 9, and handles 17 are fixedly connected to the side of the movable base 9.

[0034] Push the handle 17 on the side of the mobile base 9 and use the casters 16 below the mobile base 9 to move the entire installation equipment to the side of the aircraft wheel installation station, initially determine the basic position for the installation work, and meet the station adaptation requirements under different installation scenarios.

[0035] The robotic arm 15 is used to install the wheel hub on the installation auxiliary component 14. After the robotic arm 15 moves the wheel hub to the appropriate position, the installation auxiliary component 14 will position and clamp the wheel hub. Then, through the drive component 12 and the telescopic rod 13, the wheel hub connection part 1 is aligned with the installation position, which facilitates the worker to carry out the installation operation.

[0036] Please see Figure 7 and Figure 8The driving assembly 12 comprises a screw rod 18 threadedly connected with the adjusting seat 10, the adjusting seat 10 is provided with a sliding groove 19 in the axial direction of the screw rod 18, the bottom of the sliding bottom plate 11 is fixedly connected with a driving piece 20, the driving piece 20 is threadedly connected with the screw rod 18, the driving piece 20 is slidably connected with the sliding groove 19, and the screw rod 18 is rotationally driven by a power unit. The screw rod 18 is provided with two screw rods and is located on the two sides of the adjusting seat 10, respectively, the screw rod 18 is connected with a driven gear 21 at the end, the power unit comprises a driving motor 22 fixedly connected with the moving base 9, a driving motor 22 is fixedly connected with a driving gear 23 on the output shaft, and the driving gear 23 is engaged with the driven gear 21. The driving motor 22 is a double-output-shaft motor, the driving motor 22 is fixedly connected with the driving gear 23 on the two output ends, and the two driven gears 21 are engaged with different driving gears 23.

[0037] The device adjusts the position and height of the installation auxiliary assembly 14 in cooperation with the driving assembly 12 and the telescopic rod 13. The driving motor 22 is started, the driving motor 22 drives the driving gear 23 to rotate, thereby driving the driven gear 21 engaged with the driving gear 23 to rotate, and the screw rod 18 rotates synchronously with the driven gear 21. Since the driving piece 20 at the bottom of the sliding bottom plate 11 is threadedly connected with the screw rod 18 and slidably connected with the sliding groove 19 of the adjusting seat 10, when the screw rod 18 rotates, the driving piece 20 translates along the sliding groove 19, thereby driving the sliding bottom plate 11, the telescopic rod 13 and the installation auxiliary assembly 14 above the sliding bottom plate 11 to move horizontally and accurately until the hub connecting part 1 is aligned with the installation position of the airplane. The telescopic rod 13 is controlled to be telescopic, the installation auxiliary assembly 14 at the top of the telescopic rod 13 is adjusted in height along with the change of the length of the telescopic rod 13, and the sliding bottom plate 11 is matched to adjust the position of the hub.

[0038] Please refer to Figure 5 The installation auxiliary assembly 14 comprises a vertical plate 24 fixedly connected with the top of the telescopic rod 13, a clamping motor 25 fixedly connected with the vertical plate 24, a clamping plate 26 fixedly connected with the output shaft of the clamping motor 25, a plurality of arc-shaped grooves 27 symmetrically distributed in the clamping plate 26, the arc-shaped grooves 27 being different in distance from the output shaft of the clamping motor 25, a plurality of guide grooves 28 equally distributed on the vertical plate 24, the number of the guide grooves 28 being consistent with that of the arc-shaped grooves 27, a clamping rod 29 slidably connected with the inside of each guide groove 28, and the clamping rod 29 being located in the corresponding arc-shaped groove 27. The clamping motor 25 is provided with two groups, and the hub is fixed to the side surface of the vertical plate 24 through the clamping rod 29.

[0039] When the mechanical arm 15 moves the hub to the appropriate position, the clamping motor 25 rotates, and its output shaft drives the clamping plate 26 to rotate. Since one end of the clamping rod 29 is slidingly connected in the guide groove 28 of the vertical plate 24, and the other end is embedded in the arc-shaped groove 27 of the clamping plate 26, when the clamping plate 26 rotates, the arc-shaped groove 27 pushes the clamping rod 29 to move along the guide groove 28 towards the hub, and multiple clamping rods 29 act synchronously to stably clamp the hub on the side of the vertical plate 24, avoiding the hub from deviating during installation.

[0040] Working principle: The aircraft wheel hub core is the airflow introduction assembly 6 that guides the airflow into the air channel groove 4, and through the path formed by the air channel groove 4 and the heat dissipation channel 5, the airflow is accurately delivered to the heat core area to achieve efficient heat dissipation and ensure the stability of the wheel. When the aircraft is taxiing or taking off, the ring-shaped protrusion 8 of the airflow introduction assembly 6 is protruded on the outer surface, and the airflow speed on the outside is high and the air pressure is low. The airflow enters the air channel groove 4 through the center, flows along the preset path to the spoke 2, and then is divided into each heat dissipation channel 5. When the airflow is discharged from the end of the channel to the rim 3, it carries away the heat of the brake, avoiding the high temperature from affecting the performance or damaging the structure, and completing the active heat dissipation cycle.

[0041] Special equipment is required for installation. First, use the mechanical arm 15 to place the hub on the installation auxiliary assembly 14 to reduce the difficulty of manual work. Start the drive motor 22 to rotate the screw rod 18 through the driving gear 23 and the driven gear 21. Since the driving part 20 at the bottom of the sliding bottom plate 11 is threadedly connected with the screw rod 18 and slides in the sliding groove 19 of the adjusting seat 10, when the screw rod 18 rotates, the driving part 20 drives the sliding bottom plate 11, the upper telescopic rod 13 and the installation auxiliary assembly 14 to move horizontally and accurately, and through the cooperation of the drive motor 22 and the telescopic rod 13, the hub position calibration is completed.

[0042] The clamping motor 25 rotates, and its output shaft drives the clamping plate 26 to rotate. One end of the clamping rod 29 is slidingly connected in the guide groove 28 of the vertical plate 24, and the other end is embedded in the arc-shaped groove 27 of the clamping plate 26. When the clamping plate 26 rotates, the arc-shaped groove 27 pushes the clamping rod 29 to move along the guide groove 28 towards the hub. Multiple clamping rods 29 act synchronously to stably clamp the hub and prevent installation deviation.

[0043] It is apparent to those skilled in the art that the present application is not limited to the details of the foregoing exemplary embodiments, and that the present application can be implemented in other specific forms without departing from the spirit or essential characteristics of the present application. Therefore, the embodiments should be considered in all respects as illustrative and not restrictive, and the scope of the present application is defined by the appended claims rather than the foregoing description, and it is intended to include all changes falling within the meaning and scope of the equivalent elements of the claims. Any reference signs in the claims should not be considered as limiting the claims involved.

[0044] Furthermore, it should be understood that although the specification is described in terms of embodiments, not every embodiment includes every feature described. The specification can include implicit combinations of explicitly mentioned features and / or explicit combinations of implicitely mentioned features. Each embodiment depends on the explicit combinations of features and / or the implicit combinations of features made specifically within that embodiment, and each such embodiment can be combined with every other such embodiment to create further embodiments.

Claims

1. An aircraft wheel hub structure comprising a hub connection portion (1), a spoke (2) and a rim (3), the rim (3) being connected to the hub connection portion (1) by the spoke (2), characterised in that, The spoke (2) is provided with an air channel groove (4), and the air channel groove (4) is provided with a heat dissipation channel (5) at the end, the heat dissipation channel (5) is located at the rim (3), and the air channel groove (4) is connected with an air flow introduction assembly (6) which introduces air flow into the air channel groove (4).

2. An aircraft wheel hub structure as claimed in claim 1, characterised in that, Each of the spokes (2) is in Y-shaped structure, and the heat dissipation channel (5) is arranged in the Y-shaped structure of the spoke (2) and communicates with the air channel groove (4).

3. An aircraft wheel hub structure as claimed in claim 1, characterised in that, The air flow introduction assembly (6) comprises a sealing plate (7), the sealing plate (7) is fixedly connected with a ring-shaped protrusion (8) on the outer side, the ring-shaped protrusion (8) communicates with the air channel groove (4), and after the sealing plate (7) is connected on the outer side of the air channel groove (4), the air channel groove (4) only communicates with the heat dissipation channel (5) and the ring-shaped protrusion (8).

4. A method of mounting an aircraft wheel hub structure as claimed in any one of claims 1 to 3, characterised in that, The method is installed by using the following equipment, the equipment comprises a movable base (9), the movable base (9) is fixedly connected with an adjusting seat (10), the adjusting seat (10) is slidably connected with a sliding bottom plate (11), the adjusting seat (10) is provided with a driving assembly (12) which drives the sliding bottom plate (11) to move, the sliding bottom plate (11) is fixedly connected with an extension rod (13) above, the extension rod (13) is fixedly connected with an installation auxiliary assembly (14) at the top, and the hub is installed through the installation auxiliary assembly (14).

5. The method of mounting an aircraft wheel hub structure according to claim 4, wherein, The movable base (9) is fixedly connected with two mechanical arms (15) above, and the movable base (9) is fixedly connected with a movable wheel (16) below.

6. The method of installing an aircraft wheel hub structure according to claim 4, wherein, The driving assembly (12) comprises a screw rod (18) which is screwed with the adjusting seat (10), the adjusting seat (10) is provided with a sliding groove (19) which is consistent with the axial direction of the screw rod (18), a driving piece (20) is fixedly connected with the bottom of the sliding bottom plate (11), the driving piece (20) is screwed with the screw rod (18), the driving piece (20) is slidably connected with the sliding groove (19), and the screw rod (18) is rotationally driven by a power unit at the end.

7. The method of installing an aircraft wheel hub structure according to claim 6, wherein, The screw rod (18) is provided with two and is located on both sides of the adjusting seat (10) respectively, the screw rod (18) is connected with a driven gear (21) at the end, the power unit comprises a driving motor (22) which is fixedly connected with the movable base (9), a driving motor (22) is fixedly connected with a driving motor (22) on the output shaft, and the driving motor (22) is fixedly connected with a driving motor (22) on the output shaft.

8. The method of installing an aircraft wheel hub structure according to claim 7, wherein, The driving motor (22) is a double-output-shaft motor, the driving motor (22) is fixedly connected with a driving motor (22) on the two output ends, and the two driven gears (21) are engaged with different driving gears (23) respectively.

9. The method of installing an aircraft wheel hub structure of claim 4, wherein, The installation auxiliary assembly (14) comprises a vertical plate (24) fixedly connected at the top of the telescopic rod (13), the vertical plate (24) is fixedly connected with a clamping motor (25), the output shaft of the clamping motor (25) is fixedly connected with a clamping plate (26), a plurality of arc-shaped grooves (27) are arranged on the clamping plate (26) and are distributed in a rotational symmetry mode, the distances from the arc-shaped grooves (27) to the output shaft of the clamping motor (25) are different, a plurality of guide grooves (28) are arranged on the vertical plate (24) and are distributed at equal angles, the number of the guide grooves (28) is consistent with that of the arc-shaped grooves (27), and the guide grooves (28) are all slidably connected with clamping rods (29) inside.

10. The method of installing an aircraft wheel hub structure according to claim 9, wherein, The clamping motor (25) is provided with two groups, and the hub is fixed to the side surface of the vertical plate (24) through the clamping rod (29).

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