CN114346614A - Method for manufacturing airplane bushing - Google Patents
Method for manufacturing airplane bushing Download PDFInfo
- Publication number
- CN114346614A CN114346614A CN202210019723.0A CN202210019723A CN114346614A CN 114346614 A CN114346614 A CN 114346614A CN 202210019723 A CN202210019723 A CN 202210019723A CN 114346614 A CN114346614 A CN 114346614A
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- positioning plate
- bushing
- bush
- plate
- rotary table
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- Jigs For Machine Tools (AREA)
Abstract
The invention discloses a method for manufacturing an aircraft bushing replica, which comprises the following steps: (1) manufacturing a positioning plate: drilling a hole with the diameter consistent with the outer diameter of the bushing in the middle of the positioning plate; (2) step processing: grinding the step of the bush to be processed; (3) clamping: placing the positioning plate on the universal rotary table, fixing the positioning plate on the universal rotary table by using the first pressure plate, placing the disassembly bushing in the positioning plate, and then pressing the disassembly bushing on the positioning plate by using the second pressure plate; (4) alignment: finding the position where the inner hole of the disassembly bush is consistent with the main shaft of the machine tool by using a dial indicator, fixing a universal rotary table, and taking down the disassembly bush; (5) boring: and (3) installing the bush processed in the step (2) into a positioning plate, and then boring. The invention can copy the same bushing according to the state of the inner hole of the original bushing, the manufactured product has good quality and simple operation, avoids the trouble caused by replacing the bushing, saves the processing cost and ensures the installation requirement of airplane parts.
Description
Technical Field
The invention belongs to the technical field of machine manufacturing, and particularly relates to a manufacturing method for copying an airplane lining.
Background
In order to ensure the structural strength of the airplane, steel bushings are required to be installed in bottom holes of the involution intersection points of the airplane aluminum parts, small allowance is reserved in bushing holes, when parts are assembled, the parts need to be coordinated and hinged to be coaxial with other parts, the bushings are difficult to assemble due to the fact that the diameters of the bushings and the excircle axis are inclined to a certain degree and eccentric after the parts are coordinated through manual reaming, and the bushings are prone to scratch and cannot be used.
Disclosure of Invention
In order to solve the problems, the invention aims to provide a manufacturing method for copying an aircraft liner.
A method of making an aircraft liner replica, 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 a hole with the aperture consistent with the outer diameter of the bushing is drilled in the middle of the positioning plate;
(2) step processing: grinding the step of the bush to be machined, wherein the thickness of the step is consistent with that of the step for disassembling the bush;
(3) clamping: the positioning plate is placed on the universal rotary table, the first pressing plate is used for fixing the positioning plate on the universal rotary table, the dismounting bush is placed in the positioning plate, then the second pressing plate is used for pressing the dismounting bush on the positioning plate, the first pressing plate and the second pressing plate are both connected to the universal rotary table through screws and nuts, and in order to guarantee reliable pressing, the bottoms of the other ends of the first pressing plate and the second pressing plate are supported by supporting rods;
(4) alignment: installing a dial indicator on the boring machine, adjusting the universal rotary table, finding the position where the inner hole of the disassembly bush is consistent with the main shaft of the machine tool by using the dial indicator, fixing the universal rotary table, loosening the second pressure plate, and taking down the disassembly bush;
(5) boring: and (3) installing the bush processed in the step (2) into a positioning plate, pressing the bush tightly through a second pressing plate, and then boring.
Compared with the prior art, the manufacturing method for copying the airplane lining has the beneficial effects that: the invention can copy the same bushing according to the state of the inner hole of the original bushing, the manufactured product has good quality and simple operation, avoids the trouble caused by replacing the bushing, saves the processing cost and ensures the installation requirement of airplane parts.
Drawings
The present invention will be described in further detail with reference to the accompanying drawings.
FIG. 1 is a schematic structural diagram of a clamping process in the manufacturing method for copying the aircraft liner according to the present invention;
fig. 2 is a top view of fig. 1.
Shown in the figure, 1-a bush to be processed, 2-a positioning plate, 3-a first pressing plate, 4-a nut, 5-a screw, 6-a second pressing plate, 7-a supporting rod and 8-a universal turntable.
Detailed Description
The following description of the embodiments of the present invention is provided for illustrative purposes, and other advantages and effects of the present invention will become apparent to those skilled in the art from the present disclosure.
It should be understood that the structures, proportions, and dimensions shown in the drawings and described herein are for illustrative purposes only and are not intended to limit the scope of the present invention, which is defined by the claims, but rather by the claims. In addition, the terms such as "upper" and "bottom" used in the present specification are for convenience of description only, and are not intended to limit the scope of the present invention, and the relative relationship between the terms and the terms is not to be construed as a scope of the present invention unless otherwise specified.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the term "connected" is to be interpreted broadly, e.g. as a fixed connection, a detachable connection, or an integral connection; can be mechanically or electrically connected; may be directly connected or indirectly connected through an intermediate. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
As shown in fig. 1 and 2, a method for manufacturing an aircraft liner replica includes 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 that of the bushing, a hole with the diameter consistent with the outer diameter of the bushing is drilled in the middle of the positioning plate 2, and the fit relationship of the positioning plate 2 and the bushing is clearance fit H7/H6;
(2) step processing: grinding the step of the bush 1 to be processed, wherein the thickness of the step is consistent with that of the step for dismounting the bush;
(3) clamping: the positioning plate 2 is placed on a universal rotary table 8, the positioning plate 2 is fixed on the universal rotary table 8 through a first pressing plate 3, a disassembly bushing is placed in the positioning plate 2, then the disassembly bushing is pressed on the positioning plate 2 through a second pressing plate 6, the first pressing plate 3 and the second pressing plate 6 are both connected to the universal rotary table 8 through a screw rod 5 and a nut 4, in order to guarantee reliable pressing, the bottoms of the other ends of the first pressing plate 3 and the second pressing plate 6 are supported by a support rod 7, waist-shaped holes are formed in the first pressing plate 3 and the second pressing plate 6 in order to adjust the positions of the first pressing plate 3 and the second pressing plate 6, the screw rod 5 is connected with the universal rotary table 8 through the waist-shaped holes, and the other end of the screw rod is fixed through the nut 4;
(4) alignment: installing a dial indicator on the boring machine, adjusting the universal rotary table 8, finding the position where the inner hole of the disassembly bush is consistent with the main shaft of the machine tool by using the dial indicator, fixing the universal rotary table 8, loosening the second pressure plate 6, and taking down the disassembly bush;
(5) boring: and (3) the bush processed in the step (2) is installed into the positioning plate 2, is tightly pressed through the second pressing plate 6, and then is bored.
Other parts of the invention not described in detail are conventional techniques known to the person skilled in the art.
The scope of the present invention is not limited to the technical solutions disclosed in the embodiments, and any modifications, equivalent substitutions, improvements, etc. made to the above embodiments according to the technical spirit of the present invention fall within the scope of the present invention.
Claims (4)
1. A manufacturing method for copying an aircraft liner is characterized by comprising the following steps:
(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 a hole with the aperture consistent with the outer diameter of the bushing is drilled in the middle of the positioning plate;
(2) step processing: grinding the step of the bush to be machined, wherein the thickness of the step is consistent with that of the step for disassembling the bush;
(3) clamping: placing the positioning plate on the universal rotary table, fixing the positioning plate on the universal rotary table by using a first pressure plate, placing the disassembly bushing in the positioning plate, then pressing the disassembly bushing on the positioning plate by using a second pressure plate, and connecting the first pressure plate and the second pressure plate to the universal rotary table through a screw and a nut;
(4) alignment: installing a dial indicator on the boring machine, adjusting the universal rotary table, finding the position where the inner hole of the disassembly bush is consistent with the main shaft of the machine tool by using the dial indicator, fixing the universal rotary table, loosening the second pressure plate, and taking down the disassembly bush;
(5) boring: and (3) installing the bush processed in the step (2) into a positioning plate, pressing the bush tightly through a second pressing plate, and then boring.
2. The method for fabricating an aircraft bushing replica as set forth in claim 1, wherein said step (1) is carried out such that the thickness of the positioning plate is 2-3mm greater than the height of the bushing.
3. The method for manufacturing the replica of the liner of the airplane as claimed in claim 1 or 2, wherein the fitting relationship between the hole in the middle of the positioning plate and the liner in the step (1) is clearance fit H7/H6.
4. The method for manufacturing the replica of the liner of the airplane as claimed in claim 3, wherein a support rod is provided at the bottom of the other end 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 true CN114346614A (en) | 2022-04-15 |
| CN114346614B CN114346614B (en) | 2023-07-25 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210019723.0A Active CN114346614B (en) | 2022-01-10 | 2022-01-10 | Manufacturing method for copying airplane bushing |
Country Status (1)
| Country | Link |
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| CN (1) | CN114346614B (en) |
Cited By (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 (11)
| 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 |
| US20070059093A1 (en) * | 2005-09-09 | 2007-03-15 | Chun Victor L | Flanged demountable pins and bushings and method of manufacture |
| 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 |
| US20140145427A1 (en) * | 2012-11-26 | 2014-05-29 | The Boeing Company | Bushings, apparatuses including bushings, and associated methods |
| 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 |
-
2022
- 2022-01-10 CN CN202210019723.0A patent/CN114346614B/en active Active
Patent Citations (11)
| 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 |
| US20070059093A1 (en) * | 2005-09-09 | 2007-03-15 | Chun Victor L | Flanged demountable pins and bushings and method of manufacture |
| 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 |
| US20140145427A1 (en) * | 2012-11-26 | 2014-05-29 | The Boeing Company | Bushings, apparatuses including bushings, and associated methods |
| 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 |
Cited By (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 |
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| Publication number | Publication date |
|---|---|
| CN114346614B (en) | 2023-07-25 |
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