CN221189106U

CN221189106U - Airplane wheel fault emergency traction device

Info

Publication number: CN221189106U
Application number: CN202322829994.5U
Authority: CN
Inventors: 王强
Original assignee: Jiangsu Lizhou Automotive Parts Co ltd
Current assignee: Jiangsu Lizhou Automotive Parts Co ltd
Priority date: 2023-10-23
Filing date: 2023-10-23
Publication date: 2024-06-21
Anticipated expiration: 2033-10-23

Abstract

The utility model belongs to the technical field of traction equipment, and particularly relates to an airplane wheel fault emergency traction device. The device comprises a bracket, a wheel holding device and a base; the support is arranged on the base through a lifting device, and universal wheels are arranged at four corners of the base; the bracket is 冂 -shaped, the opening end of the bracket is detachably provided with a fixed plate, one end of the bracket far away from the fixed plate is provided with a front baffle, and a wheel holding device is slidably arranged between the front baffle and the fixed plate; the wheel holding device comprises a rear baffle. The device hugs the aircraft wheel tightly through the front baffle and the rear baffle, lifts the aircraft wheel through the lifting device, replaces the fault aircraft wheel, and enables the aircraft to recover to have the traction capability.

Description

Airplane wheel fault emergency traction device

Technical Field

The utility model belongs to the technical field of traction equipment, and particularly provides an airplane wheel fault emergency traction device.

Background

Aircraft are increasingly becoming an indispensable tool for modern civilization, which deeply changes and affects people's lives. However, even if the aircraft is required to be re-inspected and maintained before use, the aircraft is inevitably subjected to safety failure in practical application.

Currently, the main occurrence positions of the faults of the aircraft are the front wheels of the aircraft, such as the failure of the front wheels of the aircraft to put down, the tire burst of the front wheels of the aircraft and the steering failure of the front wheels of the aircraft. When this occurs, it is desirable to immediately pull the aircraft from the runway, avoiding collision accidents and disrupting airport take-off and landing arrangements. However, because the front wheel of the aircraft cannot be used normally, a traction device needs to be provided to replace the fault wheel, so that the aircraft is restored to have the capability of being towed, and the aircraft can be separated from the runway in the shortest time.

Disclosure of utility model

The utility model aims to: in order to overcome the defects, the utility model aims to provide the airplane wheel fault emergency traction device which can lift the airplane wheel to replace the fault airplane wheel, so that the airplane can recover the traction capability, and meanwhile, various safety protection measures are provided, and the position of the baffle plate can be adjusted according to the size of the airplane wheel, so that the device is suitable for different types of airplanes.

The technical scheme is as follows: in order to achieve the above object, the present utility model provides an aircraft wheel failure emergency traction device, comprising: the device comprises a bracket, a wheel holding device and a base; the support is arranged on the base through a lifting device, the lifting device is arranged on the base, the output end of the lifting device is fixedly connected with the support, and universal wheels are arranged at four corners of the base; the bracket is 冂 -shaped, the opening end of the bracket is detachably provided with a fixed plate, one end of the bracket, which is far away from the fixed plate, is provided with a front baffle, and a wheel holding device is slidably arranged between the front baffle and the fixed plate; the wheel holding device comprises a rear baffle. In the airplane wheel fault emergency traction device, one side of an airplane wheel is abutted against the surface of a front baffle, and the other side of the airplane wheel is abutted against the surface of a rear baffle by sliding the rear baffle. After the aircraft wheel is fixed, starting a lifting device, lifting the aircraft wheel, and pulling the aircraft through the universal wheels.

Further, in the airplane wheel fault emergency traction device, the wheel holding device further comprises a sliding rail, a sliding block, a pulley and a telescopic unit; a group of sliding rails are arranged on the support, the sliding blocks are arranged on the sliding rails in a sliding manner through pulleys, the rear baffle is fixedly connected with the sliding blocks through pin shafts, and the telescopic units are fixedly connected with the sliding blocks. In the airplane wheel fault emergency traction device, the telescopic unit drives the rear baffle to slide in the sliding rail, so that the device can be suitable for airplane wheels with different sizes, and the enclasping of the airplane wheels is completed.

Further, in the airplane wheel fault emergency traction device, one side, far away from the universal wheel, of the sliding rail is provided with the positioning table, the positioning table is arranged on the support, and the sliding rail and the positioning table are provided with a group of pin holes corresponding to the positions. In the airplane wheel fault emergency traction device, the pin holes are formed in the sliding rail and the positioning table, and the wheel holding device is fixed through the positioning pins, so that the wheel holding device is prevented from moving in the traction process.

Further, in the airplane wheel fault emergency traction device, the limiting piece is arranged on the support, the limiting groove is formed in the limiting piece, the fixing block is arranged on the base, the locating pin is arranged in the fixing block in a penetrating mode, and the locating pin can be arranged in the limiting groove in a penetrating mode. In the airplane wheel fault emergency traction device, after the bracket reaches the preset height, the height of the bracket is fixed by inserting the locating pin on the base into the limit groove on the bracket.

Further, in the airplane wheel fault emergency traction device, the locating pin is provided with the safety pin at one end far away from the limiting piece, the safety pin is arranged on the locating pin in a penetrating mode, and the safety pin is located on one side, far away from the limiting piece, of the fixing block. In the airplane wheel fault emergency traction device, the locating pin can be inserted into the limit groove only by pulling out the safety pin, so that the problem that the bracket cannot be lifted due to the fact that the locating pin is mistakenly inserted into the limit groove is effectively avoided.

Further, in the airplane wheel fault emergency traction device, the rear baffle is wedge-shaped, and the bidirectional pin shaft is arranged in the rear baffle in a penetrating manner. In the airplane wheel fault emergency traction device, the bidirectional pin shafts are arranged in the rear baffle plate, so that the airplane wheel is ensured to have enough rigidity and anti-torsion transformation capacity when being clamped and lifted.

Further, in the airplane wheel fault emergency traction device, a group of clamping grooves are formed in the surfaces of the front baffle plate and the rear baffle plate, and limiting blocks can be clamped in the clamping grooves. In the airplane wheel fault emergency traction device, the limiting blocks are arranged in the clamping grooves of the front baffle plate and the rear baffle plate to fix the airplane wheel, so that the airplane wheel is prevented from turning in the migration process.

Further, the airplane wheel fault emergency traction device further comprises power distribution equipment, the power distribution equipment adopts a colloid power battery as a main power supply, and an emergency power supply system is further arranged in the power distribution equipment. The airplane wheel fault emergency traction device is powered by the colloid power battery and is provided with an emergency power supply, so that the situation that the airplane wheel falls from the traction device due to the loss of power in the migration process is prevented.

Further, in the airplane wheel fault emergency traction device, at least four lifting devices are arranged, the lifting devices are symmetrically distributed on two sides of the base, and the lifting devices are independently provided with hydraulic driving units. According to the airplane wheel fault emergency traction device, at least four lifting devices are arranged and symmetrically arranged on two sides of the base, and the independent driving units are used for controlling the device, so that cascading faults are prevented from occurring, and lifting cannot be performed or falling occurs in the middle of lifting.

The technical scheme can be seen that the utility model has the following beneficial effects: according to the airplane wheel fault emergency traction device, the airplane wheel is clamped through the front baffle and the rear baffle, so that subsequent lifting is facilitated, and meanwhile, the rear baffle can be adjusted according to the size of the airplane wheel; the positioning pin is arranged in the wheel holding device, so that the position of the rear baffle is prevented from changing in the migration process; through four independent lifting devices, the phenomenon that lifting cannot be performed due to cascading failure is prevented; the height of the bracket is fixed by arranging the limit groove and the locating pin, so that the change of the height of the machine wheel in the traction process is prevented; the safety pin is arranged on the positioning pin, so that the bracket is prevented from being lifted up due to the fact that the positioning pin is mistakenly inserted into the limiting groove; an emergency power supply is arranged in the power distribution equipment to prevent power failure in the pulling process.

Drawings

FIG. 1 is a schematic structural view of an aircraft wheel failure emergency retractor;

FIG. 2 is a top view of an aircraft wheel failure emergency retractor;

FIG. 3 is a schematic structural view of a bracket;

FIG. 4 is a schematic structural view of a wheel clasping device;

Fig. 5 is a schematic structural view of the stopper, the positioning pin and the safety pin.

In the figure: 1. a bracket; 11. a fixing plate; 12. a front baffle; 13. a positioning table; 14. a limiting piece; 23. a motor; 21. a rear baffle; 22. a slide rail; 23. a slide block; 24. a pulley; 25. a telescoping unit; 3. a power distribution device; 4. a base; 41. a lifting device; 42. a universal wheel; 43. a positioning pin; 44. a safety pin; 45. and a fixed block.

Detailed Description

The airplane wheel fault emergency traction device as shown in fig. 1 and 2 comprises a bracket 1, a wheel holding device, power distribution equipment 3 and a base 4; the bracket 1 shown in fig. 3 is arranged on the base 4 through a lifting device 41, and universal wheels 42 are arranged at four corners of the base 4; the bracket 1 is 冂, the opening end of the bracket 1 is detachably provided with a fixed plate 11, one end of the bracket 1 far away from the fixed plate 11 is provided with a front baffle 12, and a wheel holding device is slidably arranged between the front baffle 12 and the fixed plate 11; the wheel holding device comprises a rear baffle 21; the base 4 is provided with a power distribution device 3, and the power distribution device 3 is electrically connected with the lifting device 41.

Wherein, the surfaces of the front baffle 13 and the rear baffle 21 are provided with a group of clamping grooves, and limiting blocks can be clamped in the clamping grooves. The rear baffle 21 is wedge-shaped, and a bidirectional pin shaft is arranged in the rear baffle 21 in a penetrating way. The tailgate 21 is constructed of high strength steel, is wedge-shaped in design, and is locked at the bottom using a bi-directional pin to ensure adequate structural rigidity and torque-conversion capability when the wheel is clamped and lifted.

The bracket 1 is welded by using 700L and 850L high-strength structural steel 700L special for engineering vehicles, 850L low-alloy girder special steel and the like, is welded in a positioning way by using a special welding die and a positioning welding die, is welded by using argon arc welding and two-protection welding, ensures the welding strength, and is subjected to effective treatment. The whole vehicle shot blasting surface is used for removing stress and welding slag before coating, so that high torsional rigidity and whole structure toughness are ensured.

The wheel holding device shown in fig. 4 comprises a slide rail 22, a slide block 23, a pulley 24 and a telescopic unit 25; a group of slide rails 22 are arranged on the bracket 1, a slide block 23 is arranged on the slide rails 22 in a sliding way through a pulley 24, the rear baffle 21 is fixedly connected with the slide block 23 through a pin shaft, a telescopic unit 25 is fixedly connected with the slide block 23, and the telescopic unit 25 is electrically connected with the power distribution equipment 3.

Wherein the telescopic unit 25 comprises a servo motor, a two-stage reduction gearbox and an electric cylinder provided with a stroke sensor; the servo motor is powered by the power distribution equipment 3, a two-stage reduction gear box is connected to an output shaft of the servo motor, an electric cylinder is connected to an output end of the two-stage reduction gear box, and the electric cylinder is fixedly connected with the sliding block 23.

The slide rail 22 is provided with location platform 13 far away from universal wheel 41 one side, and location platform 13 installs on support 1, is provided with a set of pinhole that corresponds in position on slide rail 22 and the location platform 13. And the pulley 24 is provided with a pin. By providing locating pins on the locating table 13 and the slide rail 22 and pins on the pulley 24, the wheel holding device is prevented from sliding.

As shown in fig. 5, a limiting part 14 is arranged on the bracket 1, a limiting groove is formed in the limiting part 14, a fixed block 45 is arranged on the base 4, a positioning pin 43 is arranged in the fixed block 45 in a penetrating manner, and the positioning pin 43 can be arranged in the limiting groove in a penetrating manner. The locating pin 43 is provided with a safety pin 44 at one end far away from the limiting piece 14, the safety pin 44 is arranged on the locating pin 43 in a penetrating mode, and the safety pin 44 is located on one side, far away from the limiting piece 14, of the fixing block 45.

The power distribution equipment 3 adopts a double-circuit redundancy design, takes the actual use condition of an airport into consideration, adopts a colloid power battery as a main power supply of the equipment, adopts a 12V direct-current voltage system, and has an emergency power supply system, adopts a vehicle-mounted charger and has the functions of preventing feeding and reverse connection.

The lifting devices 41 are four and symmetrically distributed on two sides of the base 4, are arranged in an independent four-point mode, are matched with four independent tributary hydraulic driving units 42, and respectively control four-column lifting mechanisms. The lifting mechanism is a hydraulic cylinder. The output end of the hydraulic rod is abutted on the bracket 1.

The power distribution apparatus 3 is also equipped with an electrical control system capable of remotely controlling the telescopic unit 25 and the lifting device 41.

The specific use flow of the device is as follows:

1. When the airplane wheel is braked and locked or the tire is burst, the device is used by a crew of the maintenance, and is pushed to the front of the failed airplane wheel. The fixing plate 11 and the rear baffle plate 21 are taken down, the device is pushed under the failure machine wheel, and the machine wheel is fixed by using a ratchet nylon belt, so that the failure machine wheel is abutted on the front baffle plate 12.

2. The rear baffle 21 is arranged on the sliding block 23, the rotating shaft of the servo motor is controlled to rotate through the electric control system, the electric cylinder is driven to stretch and retract, the rear baffle 21 is abutted to the rear of the fault wheel, a positioning pin is arranged in a pin hole between the positioning table 13 and the sliding rail 22 in a penetrating manner, and a safety pin on the pulley 24 is locked, so that the fixing plate 11 is arranged.

3. And limiting blocks are clamped in grooves on the surfaces of the front baffle 12 and the rear baffle 21 to fix the machine wheel.

4. The lifting device 41 is controlled by the electrical control system to lift the bracket 1, and after the bracket 1 is lifted to a preset height, the safety pin 44 is pulled out, so that the positioning pin 43 is clamped in a limiting groove in the limiting piece 14 on the bracket 1.

The above embodiments are illustrative for the purpose of illustrating the technical concept and features of the present utility model so that those skilled in the art can understand the content of the present utility model and implement it accordingly, and thus do not limit the scope of the present utility model. All equivalent changes or modifications made in accordance with the spirit of the present utility model should be construed to be included in the scope of the present utility model.

Claims

1. An aircraft wheel trouble emergency traction device which characterized in that: comprises a bracket (1), a wheel holding device and a base (4); the support (1) is arranged on the base (4) through a lifting device (41), the lifting device (41) is arranged on the base (4), the output end of the lifting device (41) is fixedly connected with the support (1), and universal wheels (42) are arranged at four corners of the base (4); the support (1) is 冂 -shaped, a fixed plate (11) is detachably arranged at the opening end of the support (1), a front baffle (12) is arranged at one end, far away from the fixed plate (11), of the support (1), and a wheel holding device is slidably arranged between the front baffle (12) and the fixed plate (11); the wheel holding device comprises a rear baffle (21).

2. The aircraft wheel failure emergency traction device according to claim 1, wherein: the wheel holding device further comprises a sliding rail (22), a sliding block (23), a pulley (24) and a telescopic unit (25); a group of sliding rails (22) are arranged on the support (1), the sliding blocks (23) are arranged on the sliding rails (22) in a sliding mode through the pulleys (24), the rear baffle (21) is fixedly connected with the sliding blocks (23) through pin shafts, and the telescopic units (25) are fixedly connected with the sliding blocks (23).

3. The aircraft wheel failure emergency traction device according to claim 2, wherein: the positioning table (13) is arranged on one side, far away from the universal wheel (42), of the sliding rail (22), the positioning table (13) is arranged on the support (1), and a group of pin holes corresponding to the positions are formed in the sliding rail (22) and the positioning table (13).

4. The aircraft wheel failure emergency traction device according to claim 1, wherein: be provided with locating part (14) on support (1), the spacing groove has been seted up on locating part (14), be provided with fixed block (45) on base (4), wear to be equipped with locating pin (43) in fixed block (45), locating pin (43) can wear to establish in the spacing groove.

5. The aircraft wheel failure emergency traction device according to claim 4, wherein: the locating pin (43) is provided with a safety pin (44) at one end far away from the limiting piece (14), the safety pin (44) is arranged on the locating pin (43) in a penetrating mode, and the safety pin (44) is located on one side, far away from the limiting piece (14), of the fixing block (45).

6. The aircraft wheel failure emergency traction device according to claim 1, wherein: the rear baffle (21) is wedge-shaped, and a bidirectional pin shaft is arranged in the rear baffle (21) in a penetrating manner.

7. The aircraft wheel failure emergency traction device according to claim 1, wherein: the surfaces of the front baffle (12) and the rear baffle (21) are provided with a group of clamping grooves, and limiting blocks can be clamped in the clamping grooves.

8. The aircraft wheel failure emergency traction device according to claim 1, wherein: the airplane wheel fault emergency traction device further comprises power distribution equipment (3), the power distribution equipment (3) adopts a colloid power battery as a main power supply, and an emergency power supply system is further arranged in the power distribution equipment (3).

9. The aircraft wheel failure emergency traction device according to claim 1, wherein: at least four lifting devices (41) are arranged, the lifting devices (41) are symmetrically distributed on two sides of the base (4), and the lifting devices (41) are independently provided with hydraulic driving units.