CN101074701A - Double-eccentric bushing and its adjustment - Google Patents
Double-eccentric bushing and its adjustment Download PDFInfo
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- CN101074701A CN101074701A CN 200710123465 CN200710123465A CN101074701A CN 101074701 A CN101074701 A CN 101074701A CN 200710123465 CN200710123465 CN 200710123465 CN 200710123465 A CN200710123465 A CN 200710123465A CN 101074701 A CN101074701 A CN 101074701A
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- eccentric
- eccentric bushing
- eccentric bush
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Abstract
The invention relates to a mechanical components industry regulation hole coaxial between the methodology and regulation components, in particular the aviation, aerospace, civil and other mechanical structure of the multi-hinge assembly point. Double eccentric bushing from the eccentric bushing and the eccentric bushing composition, the eccentric bushing diameter and the outer diameter of a round circle of eccentric and the eccentric bushing diameter and the outer diameter of a round of the same circle of eccentric, and, Bushing end of the shaft is the first shoulder. Double eccentric bushing used in the eccentric bushing and the eccentric bushing with a certain amount of tolerance, through the inner and outer sleeve of repeated eccentric rotation adjustment can be realized coaxial connection points more than the match, and for each hub Heart of the biggest angle adjustment of not more than 360 degrees, adjust volume small. This greatly reduces the difficulty of assembling and because of the internal and external sleeve with tolerance, as well as components and assembly hub between the matching hole in the machining tolerances can be very good at that in the assembly, so there is no need to conduct a follow-up processing, reducing assembly time.
Description
Technical field: the double-eccentric bushing and the regulating method that the present invention relates to adjustment hole coaxality, particularly Aeronautics and Astronautics between a kind of mechanical components industry, the many hinge points assemblings of mechanical structure such as civilian.
Background technique: in practical engineering application, have many situations need adopt eccentric bush to realize the tolerance coupling of many articulating points.Traditional eccentric bush need be got full pattern at the scene, carries out following process again, and single eccentric bush can only realize being the adjustment on the long circular arc of center of circle certain radius with the reference point that the tolerance regulation range is that alignment is regulated.Do the time-consuming consumption power of operation like this, and cause lining to add the worker repeatedly possibly.In addition, if when lining need be changed, need line again, success can't once be assembled in the location, and this increases time cost and the difficulty that more changes jobs greatly.
Summary of the invention
The double-eccentric bushing and the regulating method of the workload the when porous that the purpose of this invention is to provide a kind of reduction has coaxality to require is assembled.Technical solution of the present invention is, double-eccentric bushing is made up of interior eccentric bush and outer eccentric bush, the external diameter circle of outer eccentric bush is identical with the offset of internal diameter circle offset round with the external diameter of interior eccentric bush and the internal diameter circle, and there is the lining shoulder termination of interior eccentric bush and external bushing.One end of interior eccentric bush, outer eccentric bush has the shaft shoulder, and the other end is a chamfering.The internal diameter circle of described outer eccentric bush is identical with the external diameter circle of interior eccentric bush.The internal diameter circle of outer eccentric bush is straight hole or taper hole.The external diameter circle of interior eccentric bush is for cylindrical or conical.The method of regulating coaxality is to carry out the adjusting of hole coaxality by the mutual rotation of inside and outside eccentric bush.The shaft shoulder by interior external bushing or the termination high scale that does not have a shaft shoulder realize regulating location and regulated quantity calculating.
The present invention has following beneficial effect than prior art:
Eccentric bush and outer eccentric bush were by after certain tolerance fit in double-eccentric bushing adopted, the coupling that just can realize a plurality of tie points of coaxality is regulated in rotation repeatedly by inside and outside eccentric bush, and the theoretical angle of swing during each lining aligning is no more than 180 degree, actual maximal regulated angle also is no more than 360 degree, and regulated quantity is very little.This has reduced assembling difficulty greatly, in addition because the fit tolerance of interior external bushing, and the coupling tolerance between bush assembly and the pilot hole just can well guarantee in part processing, so need not carry out following process again when assembling, reduced installation time.And when resleeve more, can integral replacing double-eccentric bushing assembly, the assembly external diameter cooperates by unit bore system with mounting hole, can realize good tolerance fit, and the accumulation of error can be regulated with the rotation of the interior external bushing of crossing double-eccentric bushing, thereby realizes the tolerance adjusting easily.
Description of drawings:
Fig. 1 is the schematic representation of the outer eccentric bush of the present invention;
Fig. 2 is the schematic representation of eccentric bush in the present invention;
Fig. 3 is the inside and outside eccentric bush combination of a present invention schematic representation;
Fig. 4 is a coaxality regulative mode schematic representation of the present invention;
Fig. 5 is the combination generalized section of cone shape hole eccentric bush of the present invention;
Fig. 6 is an application schematic representation of the present invention.
Embodiment:
Describe in detail according to Principles of Regulation of the present invention and the structural type relevant below in conjunction with accompanying drawing with adjusting.
Double-eccentric bushing is made up of interior eccentric bush 10 and outer eccentric bush 9, the offset of external diameter of outer eccentric bush 9 round 2 and internal diameter circle 1 is identical with the offset of the external diameter circle 6 of interior eccentric bush 10 and internal diameter circle 5, and the two ends of interior eccentric bush 10 and outer eccentric bush 9 has the shoulder of lining 3.Interior eccentric bush 10 and outer eccentric bush 9 can also be that an end has lining shoulder 3, and the other end is chamfering 4 and chamfering 8.The internal diameter circle 1 of outer eccentric bush 9 is measure-alike with the external diameter circle 6 of interior eccentric bush 10.The internal diameter circle 1 of outer eccentric bush 9 is straight hole or taper hole.The external diameter of interior eccentric bush 10 circle 6 and the internal diameter of outer eccentric bush 9 are justified 1 and be should be cylindrical or conical relatively.There is scale 12 termination of neck bush 10, and the termination of external bushing is scale 13 again, and the method for regulating coaxality is to carry out the adjusting of hole coaxality by the mutual rotation of interior eccentric bush 10 and outer eccentric bush 9.
Shown in Figure 1 is the outer eccentric bush 9 that is used to regulate coaxality, and there is certain offset R in the external diameter circle 2 of outer eccentric bush 9 and the center of circle of internal diameter circle 1, and outer lining is with lining shoulder 3, and the inlet end of outer eccentric bush 9 has chamfering 4.
Shown in Figure 2 is the interior eccentric bush 10 that is used to regulate coaxality, and there is certain offset r in the external diameter circle 6 of interior eccentric bush and the center of circle of internal diameter circle 5, and liner is with lining shoulder 7, and the inlet end of lining has chamfering 8.
Shown in Figure 3 is the coaxality adjusting part that interior external bushing 10 and external bushing 9 constitute, the equal diameters of the internal diameter circle 1 of outer eccentric bush 9 and the external diameter circle 6 of interior eccentric bush 10, and interior eccentric bush 10 is inserted in the outer eccentric bush 9.
In illustrating and utilize, Fig. 4 carries out the mode that coaxality is regulated after eccentric bush 10 and 9 combinations of outer eccentric bush, the offset R of outer eccentric bush 9 equates with the offset r of interior eccentric bush, the coaxality adjusting in the mutual rotation by inside and outside eccentric bush has realized in radius is the disk of 2r (2R) arbitrarily a bit.
Fig. 5 illustrates the double-eccentric bushing of cone shape hole form, and the inner diameter hole of external bushing 9 is a cone shape hole, and the external diameter face cone degree of neck bush 10 is identical with external bushing 9 hole tapers, and can fit by face, and inside and outside bush assembly is linked in the nipple orifice 11.
Fig. 6 illustrates and utilizes the double-eccentric bushing assembly to regulate the application examples of coaxality, when the suitable many hinge points of this technology connect coaxality is had the occasion of requirement, such as big hatch door joint, and the revolute pair assembling between parts.Utilize the eccentric bush assembly in the eccentric bush form pie graph 3 of Fig. 1, Fig. 2, adopt the regulating method among Fig. 4, can realize the ideal fit among Fig. 6.
Embodiment one
In the wing flap supporting structure of aircraft, articulating point is three.In the mounting hole of two articulating points, be respectively charged into two double-eccentric bushings that are assembled into one therein, the inner diameter hole of outer eccentric bush is a straight hole; At first record the axis based error of two holes and datum hole, calculate the regulated quantity of double-eccentric bushing, utilize the scale indication of lining termination again, rotate inside and outside lining mutually, regulate coaxality.
Embodiment two
In the wing flap supporting structure of aircraft, articulating point is four.In the mounting hole of three articulating points, be respectively charged into two double-eccentric bushings that are assembled into one therein, the inner diameter hole of outer eccentric bush is a conical bore, and the outer diametric plane of neck bush also is a conical bore; At first record the axis based error of two holes and datum hole, calculate the regulated quantity of double-eccentric bushing, utilize the scale indication of lining termination again, rotate inside and outside lining mutually, regulate coaxality.
Claims (7)
1. double-eccentric bushing, it is characterized in that, double-eccentric bushing is made up of interior eccentric bush and outer eccentric bush, and the external diameter circle of outer eccentric bush is identical with the offset of internal diameter circle offset round with the external diameter of interior eccentric bush and the internal diameter circle, and there is the lining shoulder termination of inside and outside eccentric bush.
2. double-eccentric bushing according to claim 1 is characterized in that, an end of inside and outside eccentric bush has the lining shoulder, and the other end is a chamfering.
3. double-eccentric bushing according to claim 1 is characterized in that, the internal diameter circle of described outer eccentric bush is identical with the external diameter circle of interior eccentric bush.
4. double-eccentric bushing according to claim 1 is characterized in that, the internal diameter circle of outer eccentric bush is straight hole or taper hole.
5. double-eccentric bushing according to claim 1 is characterized in that, the external diameter circle of interior eccentric bush is for cylindrical or conical.
6. utilize the described double-eccentric bushing of claim 1 to regulate the method for coaxality, it is characterized in that described method is to carry out the adjusting of hole coaxality by the mutual rotation of inside and outside eccentric bush.
7. double-eccentric bushing according to claim 6 is regulated the method for coaxality, it is characterized in that, the shaft shoulder by interior external bushing or the termination high scale that does not have a shaft shoulder realize regulating location and regulated quantity calculating.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200710123465 CN101074701A (en) | 2007-06-26 | 2007-06-26 | Double-eccentric bushing and its adjustment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200710123465 CN101074701A (en) | 2007-06-26 | 2007-06-26 | Double-eccentric bushing and its adjustment |
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| Publication Number | Publication Date |
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| CN101074701A true CN101074701A (en) | 2007-11-21 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN 200710123465 Pending CN101074701A (en) | 2007-06-26 | 2007-06-26 | Double-eccentric bushing and its adjustment |
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| CN (1) | CN101074701A (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102794345A (en) * | 2012-08-29 | 2012-11-28 | 绍兴文理学院 | Eccentric mechanism of vertical type numerical control rotary pressing machine |
| CN103541128A (en) * | 2013-10-16 | 2014-01-29 | 青岛天一集团红旗纺织机械有限公司 | Warp loosening device of air-jet loom |
| CN104500552A (en) * | 2014-10-09 | 2015-04-08 | 上海奥林汽车安全系统有限公司 | Pin structure for preventing hinge lining self-lubricating layer shedding |
| CN109505807A (en) * | 2017-09-15 | 2019-03-22 | 株式会社东芝 | Mounting structure, rotating machinery, air-conditioning device and adjusting method |
| CN109562428A (en) * | 2016-07-28 | 2019-04-02 | 皇冠包装技术公司 | The alignment of tank ontology manufacturing machine jumper bar |
| CN109881591A (en) * | 2019-04-04 | 2019-06-14 | 徐慧云 | The reversed stretch-draw prestressing force anchorage of carbon fiber board |
| CN111720435A (en) * | 2019-03-18 | 2020-09-29 | 成都飞机工业（集团）有限责任公司 | Device for adjusting erecting eccentricity of airplane |
| DE102020128089A1 (en) | 2020-10-26 | 2022-04-28 | Airbus Operations Gmbh | Aircraft component positioning bushing, mounting arrangement and aircraft structure |
| US11608855B2 (en) | 2021-04-16 | 2023-03-21 | The Boeing Company | Tooling and methods for clocking dual eccentric bushings of a clevis |
-
2007
- 2007-06-26 CN CN 200710123465 patent/CN101074701A/en active Pending
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102794345A (en) * | 2012-08-29 | 2012-11-28 | 绍兴文理学院 | Eccentric mechanism of vertical type numerical control rotary pressing machine |
| CN103541128A (en) * | 2013-10-16 | 2014-01-29 | 青岛天一集团红旗纺织机械有限公司 | Warp loosening device of air-jet loom |
| CN104500552A (en) * | 2014-10-09 | 2015-04-08 | 上海奥林汽车安全系统有限公司 | Pin structure for preventing hinge lining self-lubricating layer shedding |
| CN104500552B (en) * | 2014-10-09 | 2017-02-08 | 上海奥林汽车安全系统有限公司 | Pin structure for preventing hinge lining self-lubricating layer shedding |
| CN109562428A (en) * | 2016-07-28 | 2019-04-02 | 皇冠包装技术公司 | The alignment of tank ontology manufacturing machine jumper bar |
| CN109562428B (en) * | 2016-07-28 | 2022-04-01 | 皇冠包装技术公司 | Can body maker ram alignment |
| CN109505807A (en) * | 2017-09-15 | 2019-03-22 | 株式会社东芝 | Mounting structure, rotating machinery, air-conditioning device and adjusting method |
| CN111720435A (en) * | 2019-03-18 | 2020-09-29 | 成都飞机工业（集团）有限责任公司 | Device for adjusting erecting eccentricity of airplane |
| CN109881591A (en) * | 2019-04-04 | 2019-06-14 | 徐慧云 | The reversed stretch-draw prestressing force anchorage of carbon fiber board |
| DE102020128089A1 (en) | 2020-10-26 | 2022-04-28 | Airbus Operations Gmbh | Aircraft component positioning bushing, mounting arrangement and aircraft structure |
| US11608855B2 (en) | 2021-04-16 | 2023-03-21 | The Boeing Company | Tooling and methods for clocking dual eccentric bushings of a clevis |
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