CN217455510U

CN217455510U - Novel airplane front wheel

Info

Publication number: CN217455510U
Application number: CN202220722772.6U
Authority: CN
Inventors: 李倩; 李国胜; 陈平亮
Original assignee: Xian Aviation Brake Technology Co Ltd
Current assignee: Xian Aviation Brake Technology Co Ltd
Priority date: 2022-03-31
Filing date: 2022-03-31
Publication date: 2022-09-20
Anticipated expiration: 2032-03-31

Abstract

The application provides wheel before novel aircraft, novel preceding wheel includes: the wheel comprises an inner half wheel hub (1), an outer half wheel hub (2), a clamping ring (3), a sealing ring (4), a high-strength bolt (5), a gasket (6), a flat gasket (7), a self-locking nut (8) and the like. The novel preceding wheel is synthesized and is considered requirements such as weight, life-span, bearing capacity, seaworthiness and maintainability, utilizes emulation analysis and experimental means to carry out configuration optimization design, and very big degree has promoted wheel hub bearing capacity and fatigue life, and novel preceding wheel is furnished with the interior fender oil ring subassembly that has the overvoltage protection valve subassembly that improves the safety guarantee effect and scalable installation maintenance convenience, has improved security, reliability, maintainability and the seaworthiness of product.

Description

Novel airplane front wheel

Technical Field

The invention relates to the field of machinery, in particular to a novel airplane front wheel.

Background

At present, with the development of social economy, transportation type airplanes put forward higher and higher requirements on the weight, service life, bearing capacity, seaworthiness and maintainability of wheels, and a novel front wheel with an overvoltage protection valve is developed according to the requirements on the functions, performance, seaworthiness and the like of a front wheel of a certain airplane. The front wheel optimizes the structural design in order to meet the requirements of weight, service life, bearing capacity, seaworthiness, maintainability and the like, and is matched with an overvoltage protection valve component with the function of improving safety guarantee and an inner oil retainer ring component which is telescopic, installed and maintained conveniently.

The utility model with the application number of CN201820015260.X discloses a front airplane wheel for airplane sliding and supporting, which adopts a single-spoke-plate structure and consists of a hub, a movable rim, a half-clamping ring, a bearing, an inflating valve and the like. Compared with the airplane wheel with a split structure, the airplane wheel with the structure has poor bearing capacity, meanwhile, the installation and maintenance performance of the installed oil deflector ring is poor, and an overpressure protection valve assembly for preventing the tire from being automatically deflated due to overlarge pressure is not installed, so that the requirements on seaworthiness and safety can not be met.

The utility model discloses in the application number CN201971153U mention a preceding wheel, this wheel adopts single radials structure, comprises wheel hub, activity rim, half snap ring, tapered roller bearing, inflating valve, interval bush, drive gear, bracket component etc.. The airplane wheel is not provided with an oil retaining ring assembly in a bearing, and is not provided with an overpressure protection valve assembly for preventing the tire from being automatically deflated due to overlarge pressure, so that the requirements on seaworthiness and safety cannot be met.

Disclosure of Invention

The application provides a novel preceding wheel both satisfies aircraft function, performance requirement, satisfies aircraft seaworthiness and maintainability requirement again.

The technical scheme of the invention is as follows: the application provides wheel before novel aircraft, novel preceding wheel includes: inner half wheel hub 1, outer half wheel hub 2, rand 3, sealing washer 4, high strength bolt 5, first gasket 6, flat gasket 7, self-locking nut 8, balance weight 9, second gasket 10, outer oil retaining ring subassembly 11 of outside bearing, inner oil retaining ring subassembly 12 of outside bearing, outer oil retaining ring subassembly 13 of inside bearing, inner oil retaining ring subassembly 14 of outside bearing, cylinder head bolt 15, hexagon head nut 16, inflating valve subassembly 17, outer bearing inner circle 18, outer bearing outer circle 19, inside bearing outer circle 20, inside bearing inner circle 21 and overvoltage protection valve subassembly 22, wherein:

the inner half wheel hub 1 and the outer half wheel hub 2 are fixedly connected through a high-strength bolt 5, a first gasket 6, a flat gasket 7 and a self-locking nut 8, a sealed space is formed with a tire through a sealing ring 4, and an inflating valve assembly 17 is installed on the outer half wheel hub 2; an overpressure protection valve assembly 22 is arranged at the symmetrical position of the outer half hub 2 where the valve assembly 17 is arranged; the outer bearing inner ring 18 and the outer bearing outer ring 19 form an outer bearing, the inner bearing inner ring 21 and the inner bearing outer ring 20 form an inner bearing, the outer bearing is arranged on the outer half hub 2, the inner bearing is arranged on the inner half hub 1, the outer rings of the outer bearing and the inner bearing are connected with the wheel hub, and the inner rings of the outer bearing and the inner bearing are connected with the landing gear shaft; two ends of the outer bearing and the inner bearing are respectively provided with an oil retainer ring assembly, and the oil retainer ring assembly comprises an outer bearing outer oil retainer ring assembly 11, an outer bearing inner oil retainer ring assembly 12, an inner bearing outer oil retainer ring assembly 13 and an inner bearing inner oil retainer ring assembly 14; the outer bearing outer oil retainer ring assembly (11) is fixed by a retainer ring (3).

Specifically, the burst pressure value of the overpressure protection valve assembly 22 is set according to the tire inflation pressure value of the wheel.

Specifically, the burst pressure value of the overpressure protection valve assembly 22 is 2 to 3 times of the inflation pressure value of the tire of the airplane wheel.

Specifically, the inner diameters of the outer bearing and the inner bearing are different.

Specifically, interior half wheel hub 1 and outer half wheel hub 2 are connected fixedly through high strength bolt 5, first gasket 6, flat gasket 7, self-locking nut 8, include: the opposite face equipartition of half wheel hub 1 in and half wheel hub 2 has put the bolt hole of the same quantity, and high strength bolt 5 and first gasket 6 pass half wheel hub 1 in and half wheel hub 2's bolt hole, from half wheel hub 2 direction installation plain washer 7 of outside, fasten through self-locking nut 8.

Specifically, the outer bearing inner oil slinger assembly 12 and the inner bearing inner oil slinger assembly 14 use springs as the skeleton.

Specifically, the hub mouths of the inner half hub 1 and the outer half hub 2 are provided with protrusions and the spoke plate angle is reasonably set.

Specifically, the balance pieces 9 are mounted on the inner half hub 1 by means of the cylindrical head bolts 15, the hexagonal head nuts 16, and the second washers 10.

In conclusion, the invention provides a novel front wheel, the split structure is adopted, the inner half wheel hub 1 and the outer half wheel hub 2 are main force bearing components of the wheel, the factors such as strength, rigidity, weight, service life and the like are fully considered during design to carry out the multidisciplinary optimization of the wheel, the structural design is carried out according to the contact pressure distribution rule of the tire and the wheel rim profile and the wheel load transmission rule, particularly the slope design of the bulge at the tire foot part and the web plate part, and the bearing capacity and the fatigue life of the wheel hub are greatly improved. Meanwhile, the installed overpressure protection valve can reduce the possibility of tire explosion, the spring type oil deflector ring framework can ensure that the oil deflector ring is convenient to disassemble and install, and the safety and the maintainability of products are improved.

Drawings

Fig. 1 is a cross-sectional view of a novel front wheel provided by the present application;

FIG. 2 is a right side view of a novel front wheel provided by the present application;

wherein: 1-inner half wheel hub, 2-outer half wheel hub, 3-clamping ring, 4-sealing ring, 5-high-strength bolt, 6-first gasket, 7-flat gasket, 8-self-locking nut, 9-balance sheet, 10-second gasket, 11-outer side bearing outer oil retaining ring component, 12-outer side bearing inner oil retaining ring component, 13-inner side bearing outer oil retaining ring component, 14-inner side bearing inner oil retaining ring component, 15-cylindrical head bolt, 16-hexagonal head nut, 17-air valve component, 18-outer side bearing inner ring, 19-outer side bearing outer ring, 20-inner side bearing outer ring, 21-inner side bearing inner ring and 22-overpressure protection valve component.

Detailed Description

The invention relates to a novel airplane front wheel which is arranged on a shaft of a front landing gear of an airplane and is used for taking off, landing and running, sliding and supporting the airplane.

As shown in fig. 1 and 2, the present application provides a novel airplane front wheel, which includes: inner half wheel hub 1, outer half wheel hub 2, rand 3, sealing washer 4, high strength bolt 5, first gasket 6, flat gasket 7, self-locking nut 8, balance weight 9, second gasket 10, outer oil retaining ring subassembly 11 of outside bearing, inner oil retaining ring subassembly 12 of outside bearing, outer oil retaining ring subassembly 13 of inside bearing, inner oil retaining ring subassembly 14 of outside bearing, cylinder head bolt 15, hexagon head nut 16, inflating valve subassembly 17, outer bearing inner circle 18, outer bearing outer circle 19, inside bearing outer circle 20, inside bearing inner circle 21 and overvoltage protection valve subassembly 22, wherein:

the inner half wheel hub 1 and the outer half wheel hub 2 are fixedly connected through a high-strength bolt 5, a first gasket 6, a flat gasket 7 and a self-locking nut 8, a sealed space is formed with a tire through a sealing ring 4, and an inflating valve assembly 17 is installed on the outer half wheel hub 2; an overpressure protection valve assembly 22 is arranged at the symmetrical position of the outer half hub 2 where the valve assembly 17 is arranged; the outer bearing inner ring 18 and the outer bearing outer ring 19 form an outer bearing, the inner bearing inner ring 21 and the inner bearing outer ring 20 form an inner bearing, the outer bearing is arranged on the outer half hub 2, the inner bearing is arranged on the inner half hub 1, the outer rings of the outer bearing and the inner bearing are connected with the wheel hub, and the inner rings of the outer bearing and the inner bearing are connected with the landing gear shaft; oil deflector ring components are respectively installed at two ends of the outer side bearing and the inner side bearing, the oil deflector ring components comprise an outer oil deflector ring component 11 of the outer side bearing, an inner oil deflector ring component 12 of the outer side bearing, an outer oil deflector ring component 13 of the inner side bearing and an inner oil deflector ring component 14 of the inner side bearing, and the outer oil deflector ring component 11 of the outer side bearing is fixed through a clamping ring 3.

Preferably, the burst pressure value of the overpressure protection valve assembly 22 is 2 to 3 times the inflation pressure value of the tire of the airplane wheel.

Note that the seal ring 4 forms a closed space with the tire, and the valve assembly 17 is used to perform inflation and deflation.

It should be noted that the overpressure protection valve assembly 22 is used for realizing automatic deflation when the tire inflation pressure is too high, preventing tire burst, improving the safety of the aircraft, and meeting the requirements of airworthiness and static balance.

It should be noted that the inside diameters of the outboard bearing and the inboard bearing are different in size, so that the outboard bearing and the inboard bearing can be prevented from being mistakenly installed when being installed on the landing gear.

It should be noted that, the oil baffle ring assembly can keep the life of bearing, prevents that external debris from getting into the bearing and lubricating grease throws out.

It can be understood that the outer bearing inner oil slinger assembly 12 and the inner bearing inner oil slinger assembly 14 adopt springs as frameworks, and the telescopic characteristic of the springs can be used for installation and maintenance, so that the maintainability of the airplane is greatly improved.

Specifically, the structures of the inner half hub 1 and the outer half hub 2 are determined according to the wheel bearing load value, the service life value and the like. The hub mouths of the inner half hub 1 and the outer half hub 2 are provided with bulges for improving the strength, rigidity and fatigue life of the inner half hub 1 and the outer half hub 2.

Specifically, the web angle is determined according to a load transfer path determined by a test and a simulation analysis means.

It should be noted that the balance piece 9, the second spacer 10, the cylindrical head bolt 15 and the hexagonal head nut 16 are installed, so that the static balance requirement of the wheel can be met.

To sum up, this application provides a novel wheel before aircraft, adopts to open structure, and interior half wheel hub 1 and outer half wheel hub 2 are the main load part of wheel, and factors such as fully considered intensity, rigidity, weight, life-span carry out the multidisciplinary optimization of wheel during the design, according to tire and rim profile contact pressure distribution law and wheel load transmission law, carry out structural design, especially tire foot position swell and web position inclination design, and very big degree has promoted wheel hub bearing capacity and fatigue life.

Claims

1. A novel airplane front wheel is characterized by comprising: interior half wheel hub (1), outer half wheel hub (2), rand (3), sealing washer (4), high strength bolt (5), first gasket (6), flat gasket (7), self-locking nut (8), balance piece (9), second gasket (10), outer oil scraper ring subassembly (11) of outside bearing, oil scraper ring subassembly (12) in the outside bearing, outer oil scraper ring subassembly (13) of inside bearing, oil scraper ring subassembly (14) in the inside bearing, cylinder head bolt (15), hexagon head nut (16), inflating valve subassembly (17), outside bearing inner circle (18), outside bearing outer lane (19), inside bearing outer lane (20), inside bearing inner circle (21) and overvoltage protection valve subassembly (22), wherein:

the inner half wheel hub (1) and the outer half wheel hub (2) are fixedly connected through a high-strength bolt (5), a first gasket (6), a flat gasket (7) and a self-locking nut (8), a sealed space is formed by a sealing ring (4) and a tire, and an inflating valve assembly (17) is installed on the outer half wheel hub (2); an overpressure protection valve component (22) is arranged at the symmetrical position of the air valve component (17) arranged on the outer half hub (2); the outer bearing inner ring (18) and the outer bearing outer ring (19) form an outer bearing, the inner bearing inner ring (21) and the inner bearing outer ring (20) form an inner bearing, the outer bearing is arranged on the outer half hub (2), the inner bearing is arranged on the inner half hub (1), the outer rings of the outer bearing and the inner bearing are connected with the wheel hub, and the inner rings of the outer bearing and the inner bearing are connected with the landing gear shaft; two ends of the outer side bearing and two ends of the inner side bearing are respectively provided with an oil baffle ring assembly, and the oil baffle ring assembly comprises an outer side bearing outer oil baffle ring assembly (11), an outer side bearing inner oil baffle ring assembly (12), an inner side bearing outer oil baffle ring assembly (13) and an inner side bearing inner oil baffle ring assembly (14); the outer bearing outer oil deflector ring assembly (11) is secured by a collar (3).

2. A novel airplane front wheel according to claim 1, characterized in that the burst pressure value of the overpressure protection valve assembly (22) is set according to the tire inflation pressure value of the wheel.

3. The novel airplane front wheel according to claim 2, characterized in that the burst pressure value of the overpressure protection valve assembly (22) is 2-3 times of the inflation pressure value of the tire of the airplane wheel.

4. A novel aircraft nose wheel according to claim 1, characterised in that the inside diameters of the outboard and inboard bearings are of different sizes.

5. The novel airplane front wheel according to claim 1, characterized in that the opposite surfaces of the inner half wheel hub (1) and the outer half wheel hub (2) are provided with the same number of bolt holes, the high-strength bolts (5) and the first gaskets (6) pass through the bolt holes of the inner half wheel hub (1) and the outer half wheel hub (2), and the flat gaskets (7) are installed from the direction of the outer half wheel hub (2) and fastened through the self-locking nuts (8).

6. A novel aircraft nose wheel according to claim 1, characterised in that the outboard bearing inner oil slinger assembly (12) and the inboard bearing inner oil slinger assembly (14) employ springs as the skeleton.

7. The novel airplane front wheel according to claim 1, characterized in that the hub mouths of the inner half hub (1) and the outer half hub (2) are provided with protrusions and the angles of the radial plates are reasonably arranged.

8. Novel airplane front wheel according to claim 1, characterized in that the balancing piece (9) is mounted on the inner half-hub (1) by means of a cylindrical head bolt (15), a hexagonal head nut (16) and a second shim (10).