CN209875744U

CN209875744U - Composite aviation bush

Info

Publication number: CN209875744U
Application number: CN201920469939.0U
Authority: CN
Inventors: 冯玉生; 刘玲玲; 滕怀春; 李殿俊
Original assignee: Tianjin Yuhe Tiansheng Metal Products Co Ltd
Current assignee: Tianjin Yuhe Tiansheng Metal Products Co Ltd
Priority date: 2019-04-09
Filing date: 2019-04-09
Publication date: 2019-12-31
Anticipated expiration: 2029-04-09

Abstract

The utility model discloses a compound aviation bush, including neck bush and oil groove, the oil groove has all been processed to both sides about the right side of neck bush, the inside oil plug that is equipped with in right side of oil groove, oil groove and oil plug interference fit, the outer wall right-hand member of fixture block is equipped with the nut, and the nut links to each other with the equal screw thread of fixture block, the outer wall right side of fixture block is equipped with first block rubber, and first block rubber and fixture block clearance fit, first block rubber all closely laminates with outer bush and the lantern ring. This compound aviation bush through the cooperation between outer liner, endotheca, main shaft, fixture block, the lantern ring and the nut, makes and installs the interior bush into the inside back of outer liner, injects the fixture block, screws up the nut after rotating the fixture block again and can realize the rigidity of inside and outside bush, has solved the problem of the installation dismantlement difficulty of interior bush, through the cooperation between interior bush, outer liner, fixture block, second rubber block, spout and the slider, has solved the relatively poor problem of interior bush shock attenuation.

Description

Composite aviation bush

Technical Field

The utility model relates to an aviation bush technical field specifically is a compound aviation bush.

Background

The composite bushing has the characteristics of small friction coefficient, wear resistance, good corrosion resistance and oil-free lubrication, can reduce the cost, reduce the mechanical volume, avoid the phenomenon of shaft biting, reduce the mechanical noise and the like by using the product, and is widely applied to sliding parts of various machines, such as printers, elevators, textile machines, fitness equipment, hydraulic carriers, micro-motors, electromagnetic valves, automobiles, motorcycles, household machines and the like.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a compound aviation bush to solve the problem that proposes among the above-mentioned background art.

In order to achieve the above object, the utility model provides a following technical scheme: a composite aviation bush comprises an inner bush and an oil groove, wherein oil grooves are machined in the upper side and the lower side of the right side of the inner bush, an oil plug is arranged inside the right side of the oil groove, the oil groove is in interference fit with the oil plug, a main shaft is arranged inside the inner bush and is in clearance fit with the inner bush, an outer bush is arranged outside the inner bush, a plurality of second rubber blocks are arranged inside the upper end and the lower end of the outer bush and are in clearance fit with the outer bush, the second rubber blocks are clamped with the inner bush, a plurality of sliding grooves are machined inside the upper end and the lower end of the outer bush, sliding blocks are fixedly connected to the outer wall of each second rubber block and are in sliding clamping connection with the sliding grooves, a sleeve ring is fixedly connected to the right end of the outer wall of the inner bush, a first clamping groove and a second clamping groove are machined inside the upper side and the lower side of the outer bush and the sleeve ring respectively, and clamping blocks are arranged inside the first, and the fixture block is in clearance fit with the first clamping groove and the second clamping groove, the fixture block is attached to the second rubber block, the left end of the fixture block is in threaded connection with the outer bushing, the right end of the outer wall of the fixture block is provided with a nut, the nut is in threaded connection with the fixture block, the right side of the outer wall of the fixture block is provided with the first rubber block, the first rubber block is in clearance fit with the fixture block, and the first rubber block is tightly attached to the outer bushing and the lantern ring.

Preferably, oil baffle rings are fixedly connected to the inner portions of the left side and the right side of the inner bushing, the oil baffle rings are attached to the main shaft, ash scraping plates are fixedly connected to the outer sides of the inner bushing, and the ash scraping plates are in clearance fit with the main shaft.

Preferably, the left side of the nut is provided with a gasket, and the gasket is tightly attached to the nut and the lantern ring.

Preferably, handle grooves are machined in the right inner part of the oil plug.

Preferably, the outer wall of the outer lining is sprayed with antirust paint.

Preferably, the outer wall of the inner lining is processed with a plating layer.

Compared with the prior art, the beneficial effects of the utility model are that: this compound aviation bush, through the outer liner, the neck bush, the main shaft, the fixture block, cooperation between lantern ring and the nut, make with the inside back of neck bush installation outside liner, inject the fixture block, screw up the position fixation that the inside and outside bush can be realized to the nut again after rotating the fixture block, the problem of the installation dismantlement difficulty of neck bush has been solved, through the neck bush, the outer liner, the fixture block, the second block rubber, cooperation between spout and the slider, make after injecting the fixture block, the position of neck bush can be restricted to the second block rubber, and the second block rubber can carry out the shock attenuation to the neck bush, the relatively poor problem of neck bush shock attenuation has been solved.

Drawings

FIG. 1 is a schematic structural view of the present invention;

FIG. 2 is a schematic structural view of the outer bushing, the first rubber block and the fixture block in FIG. 1;

FIG. 3 is a schematic structural view of the inner bushing, the second rubber block and the fixture block in FIG. 1;

fig. 4 is a schematic structural view of the inner liner, the oil plug and the oil groove in fig. 1.

In the figure: 1. the outer bushing, 2, the inner bushing, 3, the spout, 4, the gasket, 5, the handle groove, 6, the oil groove, 7, the oil plug, 8, first block rubber, 9, the anti-rust paint, 10, the cladding material, 11, the fixture block, 12, the second block rubber, 13, the oil baffle ring, 14, the main shaft, 15, the scraping board, 16, the slider, 17, the nut, 18, the lantern ring, 19, first draw-in groove, 20, the second draw-in groove.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Referring to fig. 1-4, the present invention provides a technical solution: a composite aviation bush comprises an inner bush 2 and oil grooves 6, wherein the oil grooves 6 are respectively processed on the upper side and the lower side of the right side of the inner bush 2, lubricating oil can be supplemented into the inner bush 2 through the oil grooves 6, an oil plug 7 is arranged inside the right side of the oil groove 6, the oil plug 7 can prevent dust from entering the inner part of the oil groove 6, the oil grooves 6 and the oil plugs 7 are in interference fit, the oil plugs 7 can be installed or taken out at the right end of the oil grooves 6 through external force, a main shaft 14 is arranged inside the inner bush 2, the main shaft 14 is in clearance fit with the inner bush 2, the inner bush 2 can support the main shaft 14 in position, an outer bush 1 is arranged outside the inner bush 2 and limits the relative position of the inner bush 2 and the outer bush 1, a plurality of second rubber blocks 12 are respectively arranged on the inner sides of the upper end and the lower end of the outer bush 1, the second rubber blocks 12 are in clearance fit with the outer bush 1, the second rubber block 12 and the inner bushing 2 are clamped with each other, the second rubber block 12 can limit the position of the inner bushing 2, a plurality of sliding grooves 3 are respectively processed in the upper end and the lower end of the outer bushing 1, a sliding block 16 is fixedly connected to the outer wall of the second rubber block 12, the sliding block 16 can be driven by the second rubber block 12 to move, the sliding block 16 is in sliding clamping connection with the sliding grooves 3, the sliding grooves 3 can limit the limit position of the second rubber block 12 through the sliding blocks 16, a lantern ring 18 is fixedly connected to the right end of the outer wall of the inner bushing 2, the inner bushing 2 can support the lantern ring 18, a first clamping groove 19 and a second clamping groove 20 are respectively processed in the upper side and the lower side of the outer bushing 1 and the lantern ring 18, the first clamping groove 19 and the second clamping groove 20 can facilitate the relative position limitation of the outer bushing 1 and the lantern ring 18, a clamping block 11 is arranged in the first clamping groove 19 and the second clamping groove 20, and, the fixture block 11 can move in the first clamping groove 19 and the second clamping groove 20, the fixture block 11 is attached to the second rubber block 12, the fixture block 11 can push the second rubber block 12 to move, the left end of the fixture block 11 is in threaded connection with the outer bushing 1, the fixture block 11 can be installed with the outer bushing 1 by rotating, the right end of the outer wall of the fixture block 11 is provided with a nut 17, the nut 17 is in threaded connection with the fixture block 11, the relative position of the lantern ring 18 and the fixture block 11 can be limited by screwing down the nut 17, the right side of the outer wall of the fixture block 11 is provided with a first rubber block 8, the first rubber block 8 is in clearance fit with the fixture block 11, the first rubber block 8 can be directly taken down from the outer wall of the fixture block 11, the first rubber block 8 is tightly attached to the outer bushing 1 and the lantern ring 18, the outer bushing 1 can support the lantern ring 18 through the first rubber block 8, the oil blocking rings 13 are fixedly connected in the left and right sides of the inner bushing 2, the inner, the oil baffle ring 13 is attached to the main shaft 14, the main shaft 14 can move or rotate in the oil baffle ring 13, the oil baffle ring 13 can scrape lubricating oil which is convenient for oil injection 14, the outer side of the inner bushing 2 is fixedly connected with the dust scraper 15, the dust scraper 15 is in clearance fit with the main shaft 14, the dust scraper 15 can prevent small impurities from entering a gap between the inner bushing 1 and the main shaft 14, the left side of the nut 17 is provided with the gasket 4, the gasket 4 is tightly attached to the nut 17 and the lantern ring 18, the gasket 4 can prevent the nut 17 from damaging the lantern ring 18, the inner part of the right side of the oil plug 7 is provided with the handle groove 5, the handle groove 5 can drive the oil plug 7 to move, the outer wall of the outer bushing 1 is sprayed with antirust paint 9, the antirust paint 9 is paint formed by mixing red lead and dry oil, the service life of the outer bushing 1 is prolonged, the outer wall of the inner bushing 2 is provided with the plating layer 10, the plating layer 10 is a mixture of polytetrafluoroethylene, the wear resistance of the inner hub 2 is increased.

When the composite aviation bush is required to be used, the outer bush 1 can be fixed at a position required for supporting a main shaft 14 in aviation, after the fixation is finished, the inner bush 2 can be installed from right to left through the outer wall of the main shaft 14, the upper and lower second rubber blocks 12 are pushed outwards in the installation process, the inner bush 2 is pushed in, the fixture block 11 is inserted into the first clamping groove 19 and the second clamping groove 20 and also pushed to the limit position, the fixture block 11 can extrude the second rubber blocks 12 inwards in the pushing process, the second rubber blocks 12 are just inserted into the reserved grooves at the upper end and the lower end of the inner bush 2, then the fixture block 11 is rotated, the position is fixed with the outer bush 1 through the threads at the left end of the fixture block 11, the first rubber block 5 is placed on the outer wall of the fixture block 11 between the outer bush 1 and the lantern ring 18, then the nut 17 is screwed at the right end of the fixture block 11, so that the relative positions of the fixture block 11, the outer bush 1 and the lantern ring, in the use process of the inner lining 2, the oil plug 7 can be taken down, lubricating oil is supplemented to the outer wall of the main shaft 14 through the oil groove 6, the left oil baffle ring and the right oil baffle ring 13 can avoid waste of the lubricating oil, the dust scraper 15 can avoid small sundries from entering a gap between the main shaft 14 and the inner lining 2, when the main shaft 14 and the inner lining 2 vibrate, the second rubber block 12 in the vertical direction can absorb shock to a certain degree, if the inner lining 2 needs to be dismounted, the nut 17 and the fixture block 11 can be unscrewed and taken out, then the inner lining 2 is taken down, and the mounting can be completed by repeating the upper operation after a new inner lining 2 is taken out.

In the description of the present invention, it is to be understood that the terms "coaxial", "bottom", "one end", "top", "middle", "other end", "upper", "one side", "top", "inner", "front", "center", "both ends", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do 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, should not be construed as limiting the present invention.

In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "disposed," "connected," "fixed," "screwed" and the like are to be construed broadly, e.g., as meaning fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, and may be connected through the inside of two elements or in an interaction relationship between two elements, unless otherwise specifically defined, and the specific meaning of the above terms in the present invention will be understood by those skilled in the art according to specific situations.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims

1. The utility model provides a compound aviation bush, includes interior bush (2) and oil groove (6), its characterized in that have all been processed to both sides about the right side of interior bush (2): an oil plug (7) is arranged inside the right side of the oil groove (6), the oil groove (6) is in interference fit with the oil plug (7), a main shaft (14) is arranged inside the inner bushing (2), the main shaft (14) is in clearance fit with the inner bushing (2), the outer side of the inner bushing (2) is provided with an outer bushing (1), the inner sides of the upper end and the lower end of the outer bushing (1) are respectively provided with a plurality of second rubber blocks (12), the second rubber blocks (12) are in clearance fit with the outer bushing (1), the second rubber blocks (12) are clamped with the inner bushing (2) mutually, the inner parts of the upper end and the lower end of the outer bushing (1) are respectively provided with a plurality of chutes (3), the outer wall of each second rubber block (12) is fixedly connected with a sliding block (16), the sliding blocks (16) are clamped with the chutes (3) in a sliding manner, and the right end of the outer wall of the inner bushing (2) is fixedly connected, the upper and lower both sides of outer liner (1) and lantern ring (18) are inside to be processed respectively and to have first draw-in groove (19) and second draw-in groove (20), the inside of first draw-in groove (19) and second draw-in groove (20) is equipped with fixture block (11), and fixture block (11) and first draw-in groove (19) and second draw-in groove (20) clearance fit, fixture block (11) laminate mutually with second rubber block (12), the left end and outer liner (1) screw thread of fixture block (11) link to each other, the outer wall right-hand member of fixture block (11) is equipped with nut (17), and nut (17) link to each other with fixture block (11) equal screw thread, the outer wall right side of fixture block (11) is equipped with first rubber block (8), and fixture block (11) and first rubber block (8) clearance fit, first rubber block (8) and outer liner (1) and lantern ring (18) are all closely laminated.

2. A composite aircraft bushing according to claim 1, wherein: oil baffle rings (13) are fixedly connected to the inner portions of the left side and the right side of the inner bushing (2), the oil baffle rings (13) are attached to the main shaft (14), ash scraping plates (15) are fixedly connected to the outer sides of the inner bushing (2), and the ash scraping plates (15) are in clearance fit with the main shaft (14).

3. A composite aircraft bushing according to claim 1, wherein: the left side of nut (17) is equipped with gasket (4), gasket (4) and nut (17) and lantern ring (18) all closely laminate.

4. A composite aircraft bushing according to claim 1, wherein: and handle grooves (5) are processed in the right side of the oil plug (7).

5. A composite aircraft bushing according to claim 1, wherein: and the outer wall of the outer bushing (1) is sprayed with antirust paint (9).

6. A composite aircraft bushing according to claim 1, wherein: the outer wall of the inner bushing (2) is processed with a plating layer (10).