CN114346614B - Manufacturing method for copying airplane bushing - Google Patents
Manufacturing method for copying airplane bushing Download PDFInfo
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- CN114346614B CN114346614B CN202210019723.0A CN202210019723A CN114346614B CN 114346614 B CN114346614 B CN 114346614B CN 202210019723 A CN202210019723 A CN 202210019723A CN 114346614 B CN114346614 B CN 114346614B
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- bushing
- positioning plate
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- pressing plate
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Abstract
The invention discloses a manufacturing method for copying an airplane bushing, which comprises the following steps: (1) manufacturing a positioning plate: drilling a hole with the aperture consistent with the outer diameter of the bushing in the middle of the positioning plate; (2) machining steps: grinding the step of the bushing to be machined; (3) clamping: placing the positioning plate on the universal turntable, fixing the positioning plate on the universal turntable by using a first pressing plate, placing the dismounting bush in the positioning plate, and pressing the dismounting bush on the positioning plate by using a second pressing plate; (4) alignment: finding out the position of the inner hole of the disassembly bushing, which is consistent with the main shaft of the machine tool, by using a dial indicator, then fixing a universal turntable, and taking down the disassembly bushing; (5) boring: and (3) loading the bushing processed in the step (2) into a locating plate, and boring. The invention can duplicate the same bushing according to the inner hole state of the original bushing, the manufactured product has good quality and simple operation, the trouble caused by bushing replacement is avoided, the processing cost is saved, and the installation requirement of aircraft parts is ensured.
Description
Technical Field
The invention belongs to the technical field of machine manufacturing, and particularly relates to a manufacturing method for copying an aircraft bushing.
Background
In order to ensure the structural strength of the aircraft, steel bushings are arranged in bottom holes of the aluminum parts of the aircraft to the joint holes, a small amount of allowance is reserved in the bushing holes, the aluminum parts are required to be hinged to be coaxial with other parts in a coordinated manner when the assembly of the parts is met, the holes of the bushings after manual reaming are inclined and eccentric to a certain extent with the axis of the outer circle, the assembly is difficult, the inner holes of the bushings are scratched easily, the bushings cannot be used, if the replaced bushings are inconsistent with the original bushings, the other bushings and the parts in the bushing holes are required to be detached, the unified bushings are assembled again, the installation and coordination of the holes are repeated again, the labor capacity is high, and the working efficiency is low.
Disclosure of Invention
In order to solve the problems, the invention aims to provide a manufacturing method for copying an airplane lining.
A method of making an aircraft bushing copy comprising the steps of:
(1) Manufacturing a positioning plate: selecting a plate as a positioning plate, wherein the thickness of the positioning plate is higher than that of the bushing, and drilling a hole with the aperture consistent with the outer diameter of the bushing in the middle of the positioning plate;
(2) Machining steps: grinding the step of the bushing to be machined, wherein the thickness of the step is consistent with the thickness of the step for disassembling the bushing;
(3) Clamping: the positioning plate is placed on the universal turntable, the positioning plate is fixed on the universal turntable by the first pressing plate, the dismounting bush is placed in the positioning plate, then the dismounting bush is pressed on the positioning plate by the second pressing plate, the first pressing plate and the second pressing plate are connected on the universal turntable by the screw rod and the nut, and in order to ensure reliable compression, the bottoms of the other ends of the first pressing plate and the second pressing plate are supported by the supporting rod;
(4) Alignment: installing a dial indicator on a boring machine, adjusting a universal rotary table, finding out the position of an inner hole of a disassembly bushing, which is consistent with a main shaft of a machine tool, by using the dial indicator, then fixing the universal rotary table, loosening a pressing plate II, and taking down the disassembly bushing;
(5) Boring: and (3) loading the bushing processed in the step (2) into a positioning plate, compacting by a second pressing plate, and boring.
Compared with the prior art, the manufacturing method for copying the airplane bushing has the beneficial effects that: the invention can duplicate the same bushing according to the inner hole state of the original bushing, the manufactured product has good quality and simple operation, the trouble caused by bushing replacement is avoided, the processing cost is saved, and the installation requirement of aircraft parts is ensured.
Drawings
The invention is described in further detail below with reference to the accompanying drawings.
FIG. 1 is a schematic diagram of a clamping process in a method of manufacturing an aircraft liner copy of the present invention;
fig. 2 is a top view of fig. 1.
The figure shows that the bushing to be processed is 1-, the locating plate is 2-, the pressing plate is 3-, the nut is 4-, the screw is 5-, the pressing plate is 6-, the supporting rod is 7-and the universal turntable is 8-.
Detailed Description
Further advantages and effects of the present invention will become apparent to those skilled in the art from the disclosure of the present invention, which is described by the following specific examples.
It should be understood that the structures, proportions, sizes, etc. shown in the drawings are for illustration purposes only and should not be construed as limiting the invention to the extent that it can be practiced, since modifications, changes in the proportions, or adjustments of the sizes, which are otherwise, used in the practice of the invention, are included in the spirit and scope of the invention which is otherwise, without departing from the spirit or scope thereof. In addition, the terms such as "upper" and "bottom" are also used in the present specification for convenience of description, but are not limited to the scope of the present invention, and the changes or modifications of the relative relationship are considered to be within the scope of the present invention without any substantial modification of the technical content.
In the description of the present invention, it should be noted that, unless explicitly stated and limited otherwise, the term "connected" should be interpreted broadly, and for example, it may be a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
As shown in fig. 1 and 2, a method for manufacturing the replication of an aircraft bushing comprises the following steps:
(1) Manufacturing a positioning plate: selecting a plate as a positioning plate 2, wherein the thickness of the positioning plate 2 is 2-3mm higher than the height of the bushing, and drilling a hole with the aperture consistent with the outer diameter of the bushing in the middle of the positioning plate 2, wherein the matching relationship between the positioning plate 2 and the bushing is clearance fit H7/H6;
(2) Machining steps: grinding the step of the bushing 1 to be machined, wherein the thickness of the step is consistent with that of the step for disassembling the bushing;
(3) Clamping: the positioning plate 2 is placed on the universal turntable 8, the positioning plate 2 is fixed on the universal turntable 8 by the first pressing plate 3, the dismounting bush is placed in the positioning plate 2, then the dismounting bush is pressed on the positioning plate 2 by the second pressing plate 6, the first pressing plate 3 and the second pressing plate 6 are connected on the universal turntable 8 by the screw 5 and the nut 4, in order to ensure reliable compression, the bottoms of the other ends of the first pressing plate 3 and the second pressing plate 6 are supported by the supporting rod 7, in order to facilitate the adjustment of the positions of the first pressing plate 3 and the second pressing plate 6, waist-shaped holes are formed in the first pressing plate 3 and the second pressing plate 6, the screw 5 is connected with the universal turntable 8 by the waist-shaped holes, and the other ends of the screw 5 are fixed by the nut 4;
(4) Alignment: installing a dial indicator on a boring machine, adjusting the universal rotary table 8, finding the position of an inner hole of the disassembly bushing, which is consistent with the main shaft of the machine tool, by using the dial indicator, then fixing the universal rotary table 8, loosening the pressing plate II 6, and taking down the disassembly bushing;
(5) Boring: and (3) loading the bushing processed in the step (2) into the locating plate 2, compacting by the second pressing plate 6, and boring.
Other aspects of the invention are well known to those skilled in the art.
The protection scope of the present invention is not limited to the technical solutions disclosed in the specific embodiments, and any modification, equivalent replacement, improvement, etc. made to the above embodiments according to the technical substance of the present invention falls within the protection scope of the present invention.
Claims (4)
1. The manufacturing method of the aircraft bushing replication is characterized by comprising the following steps of:
(1) Manufacturing a positioning plate: selecting a plate as a positioning plate, wherein the thickness of the positioning plate is higher than that of the bushing, and drilling a hole with the aperture consistent with the outer diameter of the bushing in the middle of the positioning plate;
(2) Machining steps: grinding the step of the bushing to be machined, wherein the thickness of the step is consistent with the thickness of the step for disassembling the bushing;
(3) Clamping: placing the positioning plate on the universal turntable, fixing the positioning plate on the universal turntable by using a first pressing plate, placing the dismounting bush in the positioning plate, pressing the dismounting bush on the positioning plate by using a second pressing plate, and connecting the first pressing plate and the second pressing plate on the universal turntable by using a screw and a nut;
(4) Alignment: installing a dial indicator on a boring machine, adjusting a universal rotary table, finding out the position of an inner hole of a disassembly bushing, which is consistent with a main shaft of a machine tool, by using the dial indicator, then fixing the universal rotary table, loosening a pressing plate II, and taking down the disassembly bushing;
(5) Boring: and (3) loading the bushing processed in the step (2) into a positioning plate, compacting by a second pressing plate, and boring.
2. The method of manufacturing an aircraft bushing copy of claim 1, wherein the thickness of said locating plate in step (1) is 2-3mm higher than the height of the bushing.
3. The method for manufacturing the replication of the airplane lining according to claim 1 or 2, wherein the matching relationship between the hole in the middle of the positioning plate and the lining in the step (1) is clearance fit H7/H6.
4. The method for manufacturing the replication of the airplane bushing of claim 3, wherein a supporting rod is arranged at the bottom of the other ends of the first pressing plate and the second pressing plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210019723.0A CN114346614B (en) | 2022-01-10 | 2022-01-10 | Manufacturing method for copying airplane bushing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210019723.0A CN114346614B (en) | 2022-01-10 | 2022-01-10 | Manufacturing method for copying airplane bushing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114346614A CN114346614A (en) | 2022-04-15 |
| CN114346614B true CN114346614B (en) | 2023-07-25 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202210019723.0A Active CN114346614B (en) | 2022-01-10 | 2022-01-10 | Manufacturing method for copying airplane bushing |
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| Country | Link |
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| CN (1) | CN114346614B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115026527A (en) * | 2022-07-22 | 2022-09-09 | 邯郸市永年区海翔机械厂 | Method for machining bush in engine accessory casing |
Citations (9)
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|---|---|---|---|---|
| US5730560A (en) * | 1996-10-28 | 1998-03-24 | Ford Global Technologies, Inc. | Multi-step bushing retention system for rotary machine tool |
| KR20090120325A (en) * | 2008-05-19 | 2009-11-24 | 문경식 | Manufacturing method of bush for track link |
| CN102873363A (en) * | 2012-09-28 | 2013-01-16 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for processing pin hole of intermediate case lining |
| CN104625138A (en) * | 2014-12-01 | 2015-05-20 | 林维明 | Method for machining bush |
| CN109848456A (en) * | 2018-11-30 | 2019-06-07 | 安庆中船动力配套有限公司 | A kind of processing technology and special fixture of connecting rod bush hole |
| CN110370048A (en) * | 2019-08-07 | 2019-10-25 | 沈阳飞机工业（集团）有限公司 | A kind of fixture for boring machine of ears part processing inner hole |
| CN111609027A (en) * | 2020-06-03 | 2020-09-01 | 西北工业大学 | Bushing and method for compensating deviation of connecting hole of aircraft wall plate |
| CN112549381A (en) * | 2020-10-30 | 2021-03-26 | 哈尔滨飞机工业集团有限责任公司 | Detachable lining assembly of composite material mold and mounting and replacing method |
| CN113752008A (en) * | 2021-09-26 | 2021-12-07 | 成都飞机工业（集团）有限责任公司 | Eccentric bushing alignment recovery method based on alignment recovery assembly |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070059093A1 (en) * | 2005-09-09 | 2007-03-15 | Chun Victor L | Flanged demountable pins and bushings and method of manufacture |
| US8987612B2 (en) * | 2012-11-26 | 2015-03-24 | The Boeing Company | Bushings, apparatuses including bushings, and associated methods |
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2022
- 2022-01-10 CN CN202210019723.0A patent/CN114346614B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5730560A (en) * | 1996-10-28 | 1998-03-24 | Ford Global Technologies, Inc. | Multi-step bushing retention system for rotary machine tool |
| KR20090120325A (en) * | 2008-05-19 | 2009-11-24 | 문경식 | Manufacturing method of bush for track link |
| CN102873363A (en) * | 2012-09-28 | 2013-01-16 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for processing pin hole of intermediate case lining |
| CN104625138A (en) * | 2014-12-01 | 2015-05-20 | 林维明 | Method for machining bush |
| CN109848456A (en) * | 2018-11-30 | 2019-06-07 | 安庆中船动力配套有限公司 | A kind of processing technology and special fixture of connecting rod bush hole |
| CN110370048A (en) * | 2019-08-07 | 2019-10-25 | 沈阳飞机工业（集团）有限公司 | A kind of fixture for boring machine of ears part processing inner hole |
| CN111609027A (en) * | 2020-06-03 | 2020-09-01 | 西北工业大学 | Bushing and method for compensating deviation of connecting hole of aircraft wall plate |
| CN112549381A (en) * | 2020-10-30 | 2021-03-26 | 哈尔滨飞机工业集团有限责任公司 | Detachable lining assembly of composite material mold and mounting and replacing method |
| CN113752008A (en) * | 2021-09-26 | 2021-12-07 | 成都飞机工业（集团）有限责任公司 | Eccentric bushing alignment recovery method based on alignment recovery assembly |
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| Publication number | Publication date |
|---|---|
| CN114346614A (en) | 2022-04-15 |
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