CN216199816U

CN216199816U - Aircraft gyroscope main shaft bearing

Info

Publication number: CN216199816U
Application number: CN202122677483.7U
Authority: CN
Inventors: 翁世席; 公平; 马洪全; 刘本达; 王锐; 徐忠浩
Original assignee: Harbin Bearing Group Ltd
Current assignee: Harbin Bearing Group Ltd
Priority date: 2021-11-03
Filing date: 2021-11-03
Publication date: 2022-04-05
Anticipated expiration: 2031-11-03

Abstract

An aircraft gyroscope spindle bearing relates to the field of bearing processing. The utility model solves the problems that the existing gyroscope spindle bearing for the aircraft has low axial rigidity, and the oil-containing hole of the retainer is easy to block, so that the lubricating effect is poor, and the service life of the bearing is shortened. The aircraft gyroscope spindle bearing comprises an outer ring, two inner rings, two retainers and a plurality of steel balls, wherein two parallel first roller paths are processed on the inner surface of the outer ring, the two inner rings are coaxially arranged in the outer ring in parallel, a second roller path is processed on the outer surface of each inner ring, the two second roller paths on the outer surfaces of the two inner rings respectively correspond to the two first roller paths on the inner surface of the outer ring one by one, one retainer is arranged between each inner ring and the outer ring, the two retainers are coaxially arranged in parallel, the steel balls are installed in pockets of each retainer, the contact angle of each bearing is 30 degrees, and the gap between the two inner rings is 0.015-0.02 mm.

Description

Aircraft gyroscope main shaft bearing

Technical Field

The utility model relates to the field of bearing processing, in particular to an aircraft gyroscope spindle bearing.

Background

The gyroscope main shaft bearing for the aircraft is a double-row angular contact ball bearing, the working condition mainly requires high axial rigidity and low friction torque, and meanwhile, the bearing is required to be incapable of being filled with lubricating grease and has no lubricating oil system, namely, the bearing needs self-lubrication and can be in service for a long time of at least more than 10 years. The existing gyroscope main shaft bearing for the aircraft has the disadvantages that the axial rigidity is reduced in the using process, in addition, due to the abrasion of an oil-containing retainer, fragments are attached to the periphery of a pocket hole of the retainer, the oil-containing hole of the retainer is blocked, the lubricating effect is poor, meanwhile, the normal rotation of the bearing is influenced by deposits, and the service life of the bearing cannot meet the requirement.

In conclusion, the existing gyroscope spindle bearing for the aircraft has the problems that the axial rigidity is low, the oil-containing hole of the retainer is easy to block, the lubricating effect is poor, and the service life of the bearing is shortened.

SUMMERY OF THE UTILITY MODEL

The utility model aims to solve the problems that the existing gyroscope spindle bearing for an aircraft is low in axial rigidity, and oil-containing pores of a retainer are easy to block, so that the lubricating effect is poor, and the service life of the bearing is shortened, and further provides the gyroscope spindle bearing for the aircraft.

The technical scheme of the utility model is as follows:

the utility model provides an aircraft gyroscope main shaft bearing, aircraft gyroscope main shaft bearing includes outer lane 1, two inner circles 2, two holders 4 and a plurality of steel ball 3, the interior surface machining of outer lane 1 has two first raceways that parallel, two inner circles 2 coaxial set up in outer lane 1 inside side by side, the surface machining of every inner circle 2 has the second raceway, two second raceways of two inner circles 2 surfaces respectively with two first raceways one-to-one of outer lane 1 interior surface, all be equipped with a holder 4 between every inner circle 2 and the outer lane 1, two holders 4 coaxial set up side by side, and install steel ball 3 in the pocket hole of every holder 4, the bearing contact angle is 30 degrees, the clearance between two inner circles 2 is 0.015-0.02mm, the bearing degree of closure is for 0.015-0.02mm, the bearing degree of closure is

The contact curvature ratio of the steel ball 3 to the inner and outer ring channels is 1, the channel curvature coefficient is f, and f is 0.515.

Furthermore, an annular mounting flange is arranged on one side edge of the outer surface of the outer ring 1, and a plurality of assembling holes are uniformly processed on the annular mounting flange along the circumferential direction.

Furthermore, the number of the assembly holes on the annular mounting flange is four, and the annular mounting flange is detachably connected with the shell through four connecting pieces.

Further, the outer ring 1 is a bearing ring with double raceways, and a middle integral flange is arranged in the middle of the inner surface of the outer ring 1.

Furthermore, an edge rib is arranged on the outer side of the outer surface of each inner ring 2.

Further, the material of the holder 4 is polyimide.

Further, the aircraft gyroscope spindle bearing is a double-row angular contact ball bearing.

Further, the aircraft gyroscope spindle bearing is lubricated by using fluorine oil immersed in oil.

Compared with the prior art, the utility model has the following effects:

1. the aircraft gyroscope main shaft bearing can lift the gyroscope main shaft bearing, optimally increases the bearing contact angle, increases the bearing contact angle from original 25 degrees to 30 degrees, effectively improves the axial rigidity of the bearing, simultaneously adjusts the gap between the two inner rings of the bearing, and adjusts the gap between the two inner rings 2 to be 0.02mm, thereby improving the original pretightening force of the bearing and further improving the rigidity of the bearing.

2. The aircraft gyroscope main shaft bearing can be used for lifting the gyroscope main shaft bearing, reducing the bearing tightness, adjusting the contact curvature ratio of the steel ball to the inner and outer ring channels, reducing the channel curvature coefficient and effectively reducing the friction torque of the bearing.

3. The aircraft gyroscope main shaft bearing can lift the gyroscope main shaft bearing, adopts high-performance fluorine oil immersion lubrication, and immerses the finished bearing in the fluorine oil to ensure that the working surface of the bearing is fully contacted with oil, so that a small amount of fluorine oil is contained among the grooves, the steel balls and the pores of the retainer, the fluorine oil has excellent chemical stability, the retainer can effectively lubricate for more than 10 years, and the service life of the bearing is prolonged.

Drawings

Fig. 1 is a schematic structural view of an aircraft gyroscope spindle bearing of the present invention.

Detailed Description

The first embodiment is as follows: the embodiment is described with reference to fig. 1, and the aircraft gyroscope spindle bearing of the embodiment includes an outer ring 1, two inner rings 2, two retainers 4 and a plurality of steel balls 3, wherein two parallel first raceways are processed on an inner surface of the outer ring 1, the two inner rings 2 are coaxially arranged in parallel inside the outer ring 1, a second raceway is processed on an outer surface of each inner ring 2, the two second raceways on the outer surfaces of the two inner rings 2 respectively correspond to the two first raceways on the inner surface of the outer ring 1 one by one, one retainer 4 is arranged between each inner ring 2 and the outer ring 1, the two retainers 4 are coaxially arranged in parallel, the steel balls 3 are installed in pockets of each retainer 4, a bearing contact angle is 30 degrees, and a gap between the two inner rings 2 is a gap of 30 degrees0.015-0.02mm, bearing tightness of

The second embodiment is as follows: referring to fig. 1, the present embodiment is described, in which an annular mounting flange is provided at one side portion of an outer surface of an outer ring 1, and a plurality of mounting holes are uniformly formed in the annular mounting flange in a circumferential direction. So set up, the annular mounting flange of outer lane 1 can be dismantled with the casing and be connected through a plurality of connecting pieces. Other components and connections are the same as in the first embodiment.

The third concrete implementation mode: referring to fig. 1, the present embodiment will be described, in which the number of the fitting holes of the annular mounting flange is four, and the annular mounting flange is detachably connected to the housing by four connecting members. Other compositions and connections are the same as in the first or second embodiments.

The fourth concrete implementation mode: referring to fig. 1, the present embodiment will be described, in which an outer ring 1 of the present embodiment is a bearing ring having double raceways, and an intermediate integral rib is provided in the middle of the inner surface of the outer ring 1. Other compositions and connection relationships are the same as in the first, second or third embodiment.

The fifth concrete implementation mode: referring to fig. 1, the present embodiment is described, and an edge rib is provided on the outer surface of each inner ring 2. Other compositions and connection relationships are the same as those in the first, second, third or fourth embodiment.

The sixth specific implementation mode: the present embodiment will be described with reference to fig. 1, and the material of the holder 4 of the present embodiment is polyimide. Thus, the heat resistance and the low temperature resistance are excellent. Other compositions and connection relationships are the same as in the first, second, third, fourth or fifth embodiment.

The seventh embodiment: the present embodiment will be described with reference to fig. 1, and the aircraft gyroscope main shaft bearing of the present embodiment is a double-row angular contact ball bearing. So set up, can bear two-way axial load. Other compositions and connection relationships are the same as in the first, second, third, fourth, fifth or sixth embodiment.

The specific implementation mode is eight: the present embodiment will be described with reference to fig. 1, and the aircraft gyroscope main shaft bearing of the present embodiment is lubricated by using fluorine oil. By adopting the arrangement, the finished bearing is soaked in the fluorine oil for lubrication by adopting the high-performance fluorine oil, so that the working surface of the bearing is fully contacted with the oil, a small amount of fluorine oil is contained among the channel, the steel ball and the pore space of the retainer, the fluorine oil has excellent chemical stability, and the retainer can be effectively lubricated for more than 10 years. Other compositions and connection relationships are the same as those of embodiment one, two, three, four, five, six or seven.

The above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.

Claims

1. An aircraft gyroscope spindle bearing, characterized by: the aircraft gyroscope spindle bearing comprises an outer ring (1), two inner rings (2), two retainers (4) and a plurality of steel balls (3), wherein two parallel first roller paths are machined on the inner surface of the outer ring (1), the two inner rings (2) are coaxially arranged inside the outer ring (1) in parallel, a second roller path is machined on the outer surface of each inner ring (2), the two second roller paths on the outer surfaces of the two inner rings (2) are respectively in one-to-one correspondence with the two first roller paths on the inner surface of the outer ring (1), one retainer (4) is arranged between each inner ring (2) and the outer ring (1), the two retainers (4) are coaxially arranged in parallel, the steel balls (3) are installed in pockets of each retainer (4), the bearing contact angle is 30 degrees, the gap between the two inner rings (2) is 0.015-0.02mm, and the bearing contact angle is 0.015-0.02mm

The contact curvature ratio of the steel ball (3) to the inner and outer ring channels is 1, the channel curvature coefficient is f, and f is 0.515.

2. An aircraft gyroscope spindle bearing as claimed in claim 1, wherein: an annular mounting flange is arranged on one side edge of the outer surface of the outer ring (1), and a plurality of assembling holes are uniformly processed on the annular mounting flange along the circumferential direction.

3. An aircraft gyroscope spindle bearing as claimed in claim 2, wherein: the number of the assembly holes on the annular mounting flange is four, and the annular mounting flange is detachably connected with the shell through four connecting pieces.

4. An aircraft gyroscope spindle bearing according to claim 3, wherein: the outer ring (1) is a bearing ring with double raceways, and the middle part of the inner surface of the outer ring (1) is provided with a middle integral flange.

5. An aircraft gyroscope spindle bearing according to claim 4, wherein: the outer side of the outer surface of each inner ring (2) is provided with an edge flange.

6. An aircraft gyroscope spindle bearing according to claim 5, wherein: the material of the retainer (4) is polyimide.

7. An aircraft gyroscope spindle bearing as claimed in claim 1, wherein: the aircraft gyroscope main shaft bearing is a double-row angular contact ball bearing.

8. An aircraft gyroscope spindle bearing as claimed in claim 6 or claim 7 wherein: and the aircraft gyroscope main shaft bearing is lubricated by adopting fluorine oil immersion oil.