CN210153128U

CN210153128U - Hydraulic aviation bush

Info

Publication number: CN210153128U
Application number: CN201920470462.8U
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: 2020-03-17
Anticipated expiration: 2029-04-09

Abstract

The utility model discloses a hydraulic pressure aviation bush, including the steel bushing, the inner wall top rigid coupling of steel bushing has first retaining ring, the outer wall of first rubber ring and the inner wall interference fit of steel bushing, the bottom of first rubber ring and the top of second retaining ring are laminated mutually, the outer wall below rigid coupling of standpipe has the first cover body, the outer wall below of the first cover body and the top interference fit of first rubber ring. This hydraulic pressure aviation bush has played a good spacing effect between steel bushing and the standpipe, and then has avoided the hydraulic pressure aviation bush among the prior art, at the in-process of using, because the dynamics that bears is bigger, cause the unstable problem of being connected between its endotheca and the overcoat easily, the durability is strong, and then make this hydraulic pressure aviation bush when production and maintenance, the operation degree of difficulty is lower, and then reduced the operating cost, and is very convenient, so this hydraulic pressure aviation bush can satisfy people's use needs completely.

Description

Hydraulic aviation bush

Technical Field

The utility model relates to a bush technical field specifically is a hydraulic pressure aviation bush.

Background

In the moving part, because the abrasion of parts is caused by long-term friction, the parts must be replaced when the clearance between the shaft and the hole is abraded to a certain degree, so a designer selects a material with lower hardness and better wear resistance as the shaft sleeve or the bushing in the design, so the abrasion of the shaft and the seat can be reduced, when the shaft sleeve or the bushing is abraded to a certain degree to be replaced, the cost for replacing the shaft or the seat can be saved, generally, the bushing and the seat are in interference fit, and are in clearance fit with the shaft, particularly in the field of aviation, because the required precision of a workpiece is higher, and the operating environment is worse, the damage of various parts is more frequent, and in the using process of the hydraulic aviation bushing in the prior art, because the bearing force is higher, the stable connection between the inner bushing and the outer bushing can not be ensured, and the hydraulic aviation bushing is easy to be used for a long time or under a larger force, the hydraulic aviation lining is disassembled, normal use of aviation equipment is affected, the hydraulic aviation lining is produced and maintained, operation difficulty is high, operation cost is improved, and the hydraulic aviation lining is very inconvenient and cannot meet use requirements of people.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a hydraulic pressure 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 hydraulic aviation bush comprises a steel sleeve, wherein a first check ring is fixedly connected to the top of the inner wall of the steel sleeve, a vertical pipe is arranged inside the steel sleeve, a second check ring is fixedly connected to the bottom of the outer wall of the vertical pipe, a first rubber ring is in interference fit with the lower portion of the outer wall of the vertical pipe, the outer wall of the first rubber ring is in interference fit with the inner wall of the steel sleeve, the bottom of the first rubber ring is attached to the top of the second check ring, a first cover body is fixedly connected to the lower portion of the outer wall of the vertical pipe, the lower portion of the outer wall of the first cover body is in interference fit with the top of the first rubber ring, a second rubber ring is in interference fit with the upper portion of the outer wall of the vertical pipe, a threaded pipe is in threaded connection with the upper portion of the outer wall of the vertical pipe, a third check ring is fixedly connected to the top of the outer wall of the threaded pipe, and the bottom of the third check ring is attached, and a second cover body is fixedly connected above the outer wall of the vertical pipe, the upper part of the outer wall of the second cover body is in interference fit with the bottom of the second rubber ring, and an inner sleeve is fixedly connected on the inner wall of the vertical pipe.

Preferably, the thread groove has been seted up on the bottom right side of steel bushing, the inner wall right side that the steel bushing was run through bent hole in the top of thread groove, the inside threaded connection of thread groove has the threaded rod, the top rigid coupling of threaded rod has the quarter butt, the top rigid coupling of quarter butt has the rubber column, the outer wall of rubber column and the inner wall interference fit in bent hole.

Preferably, a first rubber ring is fixedly connected to the inner side of the first retainer ring.

Preferably, the bottom of the threaded pipe is fixedly connected with a second rubber ring.

Preferably, a plurality of lugs are fixedly connected to the upper and lower parts of the inner wall of the steel sleeve, and the lugs located above and below are respectively clamped with the second rubber ring and the first rubber ring.

Preferably, the right side of the inner wall of the inner sleeve is provided with a vertical groove.

Compared with the prior art, the beneficial effects of the utility model are that: the hydraulic aviation bush is characterized in that through the matching of the second retaining ring, the third retaining ring, the first rubber ring and the second rubber ring, plays a good role in limiting the position between the steel sleeve and the vertical pipe, thereby avoiding the hydraulic aviation lining in the prior art, in the using process, the problem of unstable connection between the inner sleeve and the outer sleeve is easily caused due to higher bearing force, and can not lead to the disassembly of the hydraulic aviation lining in long time or under larger force, thereby ensuring the normal use of the aviation equipment, being more durable, the hydraulic aviation bush has simple integral design structure, is more stable in work and strong in durability, and then make this hydraulic pressure aviation bush when production and maintenance, the operation degree of difficulty is lower, and then has reduced the operating cost, and is very convenient, so this hydraulic pressure aviation bush can satisfy people's use needs completely.

Drawings

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

FIG. 2 is a cross-sectional view of FIG. 1;

FIG. 3 is a schematic view showing the connection relationship between the steel jacket, the riser and the second rubber ring in FIG. 2;

fig. 4 is a schematic view of the connection relationship between the steel sleeve, the threaded rod and the short rod in fig. 2.

In the figure: 1. the steel bushing, 2, first retaining ring, 3, first rubber ring, 4, standpipe, 5, second retaining ring, 6, first rubber ring, 7, first cover body, 8, second retaining ring, 9, second rubber ring, 10, lug, 11, screwed pipe, 12, second rubber ring, 13, inner sleeve, 14, vertical groove, 15, third retaining ring, 16, curved hole, 17, threaded groove, 18, threaded rod, 19, short rod, 20, rubber column.

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 hydraulic aviation bush comprises a steel sleeve 1, when the hydraulic aviation bush is used, the outer wall of the steel sleeve 1 is directly in interference fit with the outside to be installed in a hole of a position to be installed, a first check ring 2 is fixedly connected to the top of the inner wall of the steel sleeve 1, a vertical pipe 4 is arranged inside the steel sleeve 1, a second check ring 5 is fixedly connected to the bottom of the outer wall of the vertical pipe 4, the second check ring 5 is matched with a third check ring 15 to prevent the vertical pipe 4 and the steel sleeve 1 from being separated, a first rubber ring 6 is in interference fit with the lower portion of the outer wall of the vertical pipe 4, the vertical pipe 4 and the steel sleeve 1 are sealed through the first rubber ring 6 and a second rubber ring 9, the vertical pipe 4 and the steel sleeve 1 are limited, the outer wall of the first rubber ring 6 is in interference fit with the inner wall of the steel sleeve 1, the bottom of the first rubber ring 6 is attached to the top of the second check ring 5, a first cover body 7 is fixedly connected to the lower portion of the outer wall of the vertical pipe 4, and a, The second rubber ring 9 plays a limiting role, the lower part of the outer wall of the first cover body 7 is in interference fit with the top of the first rubber ring 6, the second rubber ring 9 is in interference fit with the upper part of the outer wall of the vertical pipe 4, the outer wall of the second rubber ring 9 is in interference fit with the inner wall of the steel sleeve 1, a threaded pipe 11 is in threaded connection with the upper part of the outer wall of the vertical pipe 4, the threaded pipe 11 is in interference fit with the vertical pipe 4 so as to facilitate the disassembly and the installation of a third baffle ring 15, the top of the outer wall of the threaded pipe 11 is fixedly connected with the third baffle ring 15, the bottom of the third baffle ring 15 is attached to the top of the second rubber ring 9, a second cover body 8 is fixedly connected with the upper part of the outer wall of the vertical pipe 4, the upper part of the outer wall of the second cover body 8 is in interference fit with the bottom of the second rubber ring 9, an inner sleeve 13 is fixedly connected with the inner wall of the vertical pipe 4, the inner sleeve 13 is made of wear-resistant, the top of the thread groove 17 penetrates through the right side of the inner wall of the steel sleeve 1 through the curved hole 16, the internal thread of the thread groove 17 is connected with a threaded rod 18, the threaded rod 18 is matched with a rubber column 20, the hydraulic aviation bush can be prevented from entering dust in the steel sleeve 1 and the vertical pipe 4 during transportation, the top of the threaded rod 18 is fixedly connected with a short rod 19, the top of the short rod 19 is fixedly connected with the rubber column 20, the outer wall of the rubber column 20 is in interference fit with the inner wall of the curved hole 16, the inner side of the first check ring 2 is fixedly connected with a first rubber ring 3, the inner wall of the first rubber ring 3 can be tightly attached to a shaft which is inserted into the vertical pipe 4 from the outside, the dustproof effect is achieved, the bottom of the threaded pipe 11 is fixedly connected with a second rubber ring 12, a plurality of convex blocks 10 are fixedly connected to the upper and lower parts of the inner wall of the steel sleeve 1, the convex blocks 10 improve the tightness between the steel sleeve 1, the second rubber ring 9 and the, The first rubber ring 6 is clamped together, a vertical groove 14 is formed in the right side of the inner wall of the inner sleeve 13, and lubricating oil is stored in the vertical groove 14.

In this embodiment, when the hydraulic aviation bushing needs to be used, the first rubber ring 6 is firstly sleeved below the outer wall of the vertical pipe 4, so that the bottom of the first rubber ring 6 is attached to the top of the second retainer ring 5, the vertical pipe 4 is inserted into the steel sleeve 1, so that the first rubber ring 6 is tightly abutted to the steel sleeve 1, then the second rubber ring 9 is sleeved on the outer wall of the vertical pipe 4, then the threaded pipe 11 is in threaded connection with the vertical pipe 4, so that the bottom of the third retainer ring 15 is attached to the top of the second rubber ring 9, then the outer wall of the steel sleeve 1 is in interference fit with a reserved hole or a reserved groove of an external to-be-installed position, so as to fix the hydraulic aviation bushing, then an external to-be-installed shaft penetrates through the vertical pipe 4, so that the external to-be-installed shaft is ensured to be attached to the inner sleeve 13, then oil is injected between the inner sleeve 13 and the shaft inside of the inner sleeve, so as to lubricate the threaded, make threaded rod 18 pass through the 19 separation of driving rubber post 20 and curved hole 16 of quarter butt, afterwards with external hydraulic pressure pipe and thread groove 17 screw thread link to each other can, when normal work, first rubber ring 6 and second rubber ring 9 can play certain cushioning effect, and the effect through endotheca 13, reduce the friction between the inside axle of standpipe 4 and the work piece of steel bushing 1 outer wall.

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. A hydraulic aviation bush comprises a steel sleeve (1), and is characterized in that: the steel sleeve is characterized in that a first check ring (2) is fixedly connected to the top of the inner wall of the steel sleeve (1), a vertical pipe (4) is arranged inside the steel sleeve (1), a second check ring (5) is fixedly connected to the bottom of the outer wall of the vertical pipe (4), a first rubber ring (6) is in interference fit with the lower portion of the outer wall of the vertical pipe (4), the outer wall of the first rubber ring (6) is in interference fit with the inner wall of the steel sleeve (1), the bottom of the first rubber ring (6) is attached to the top of the second check ring (5), a first cover body (7) is fixedly connected to the lower portion of the outer wall of the vertical pipe (4), the lower portion of the outer wall of the first cover body (7) is in interference fit with the top of the first rubber ring (6), a second rubber ring (9) is in interference fit with the upper portion of the outer wall of the vertical pipe (4), the outer wall of the second rubber ring (9) is in interference fit with the inner wall of the steel sleeve (1), and a, the outer wall top rigid coupling of screwed pipe (11) has third retaining ring (15), the bottom of third retaining ring (15) and the top of second rubber ring (9) are to the laminating, the outer wall top rigid coupling of standpipe (4) has the second cover body (8), the outer wall top of the second cover body (8) and the bottom interference fit of second rubber ring (9), the inner wall rigid coupling of standpipe (4) has endotheca (13).

2. A hydraulic aeronautical liner according to claim 1, characterized in that: thread groove (17) have been seted up on the bottom right side of steel bushing (1), the inner wall right side that steel bushing (1) was run through hole (16) is bent at the top of thread groove (17), the internal thread of thread groove (17) is connected with threaded rod (18), the top rigid coupling of threaded rod (18) has quarter butt (19), the top rigid coupling of quarter butt (19) has rubber column (20), the outer wall of rubber column (20) and the inner wall interference fit of bent hole (16).

3. A hydraulic aeronautical liner according to claim 1, characterized in that: and a first rubber ring (3) is fixedly connected to the inner side of the first retainer ring (2).

4. A hydraulic aeronautical liner according to claim 1, characterized in that: and a second rubber ring (12) is fixedly connected to the bottom of the threaded pipe (11).

5. A hydraulic aeronautical liner according to claim 1, characterized in that: a plurality of lugs (10) are fixedly connected to the upper portion and the lower portion of the inner wall of the steel sleeve (1), and the lugs (10) located above and below are respectively connected with the second rubber ring (9) and the first rubber ring (6) in a clamping mode.

6. A hydraulic aeronautical liner according to claim 1, characterized in that: and a vertical groove (14) is formed in the right side of the inner wall of the inner sleeve (13).