CN102602546A - Aircraft stringer positioning method and mechanism - Google Patents
Aircraft stringer positioning method and mechanism Download PDFInfo
- Publication number
- CN102602546A CN102602546A CN2012101166734A CN201210116673A CN102602546A CN 102602546 A CN102602546 A CN 102602546A CN 2012101166734 A CN2012101166734 A CN 2012101166734A CN 201210116673 A CN201210116673 A CN 201210116673A CN 102602546 A CN102602546 A CN 102602546A
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- purlin
- long
- long purlin
- detent mechanism
- locating
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Abstract
The invention provides an aircraft stringer positioning method and mechanism. A stringer positioning mechanism is provided based on the relative positional relations between a known stringer to be positioned and two positioned stringers. The stringer positioning mechanism fixes the relative positional relations between the two positioned stringers and the stringer to be positioned, fixes the two positioned stringers on the corresponding positioning points of the stringer positioning mechanism and then fixes the stringer to be positioned on the corresponding positioning point of the stringer positioning mechanism, thus realizing positioning of the stringer to be positioned.
Description
Technical field
The application relates to the aircraft manufacturing technology, and the location that is in particular the long purlin of aircraft provides a kind of new method, a kind of utilization promptly is set has located the mechanism that the long purlin of no-fix is located in long purlin.
Background technology
Aircraft target ship mainly is made up of covering and long purlin, and aircraft target ship is made in the fitting process, is one of key factor that influences the aircraft target ship assembly quality with the accurate location of growing purlin and covering; Long purlin, location all needs special-purpose positioning fixture usually, but owing to the variation of aircraft configuration, and some adjacent long purlins different in size causes; Problem is that conventional positioning fixture location can't be used in short long purlin, and for location, short long purlin, existing wallboard assembling fixture need design various switching steady arm and locate long purlin on framework; Its drawback is more: design, the manufacturing cycle is long; Use inconvenience, do not have commonality, can only be used for the long purlin location and installation of certain.
Summary of the invention
The object of the present invention is to provide the localization method and the detent mechanism of the long purlin of a kind of aircraft.
The localization method of the long purlin of a kind of aircraft; Relative position relation, a long purlin detent mechanism between known long purlin to be positioned and two the oriented long purlins; It is characterized in that; Be provided with a plurality of long purlins locating point in the detent mechanism of described long purlin; This length purlin locating point has solidified two relative position relations of having located long purlin and long purlin to be positioned, and two oriented long purlins are fixed on the corresponding locating point of long purlin detent mechanism, longer purlin to be positioned is fixed on the location of realizing long purlin to be positioned on the corresponding locating point of long purlin detent mechanism.
The long purlin of above-mentioned aircraft detent mechanism; It is characterized in that containing long purlin compactor and long purlin locating plate; Described long purlin locating plate is provided with a group leader purlin locating notch; Long purlin compactor is fixed on the locating plate of long purlin, the long purlin on the compactor of long purlin compress a little with length purlin locating plate on the positioning groove stomion coincidence of long purlin consistent.
During use, will grow the purlin detent mechanism and be fixed on the oriented long purlin, locate the position of long purlin to be positioned again by long purlin detent mechanism.
The application's advantage is that the structure light weight is small and exquisite; Weight is no more than 1Kg; Can use flexibly, and have good versatility, reduce the special-purpose set packer of One's name is legion in traditional wallboard assembling fixture; Particularly narrow and small to the space, the place that special-purpose set packer can't be set provides the way that solves.
Below in conjunction with the embodiment accompanying drawing this application is described in further detail.
Description of drawings
Fig. 1 is the aircraft target ship structural representation.
Fig. 2 uses scheme drawing for long purlin detent mechanism.
Fig. 3 is the long purlin of an aircraft detent mechanism structural representation.
Fig. 4 is the compactor structural representation.
Numbering explanation among the figure: 1 covering; 2 have located long purlin; 3 long purlins to be positioned; 4 long purlin detent mechanisms; 5 locating notchs; 6 long purlins compress a little; 7 long purlin compactors; 8 long purlin locatings plate;
The specific embodiment
Referring to accompanying drawing, the aircraft target ship among Fig. 1 is made up of covering 1 and the long purlin that is riveted on its inboard, and there is fixing position relation three adjacent long purlins, and wherein have good positioning in two long purlins, and the 3rd long purlin needs the location.See Fig. 2; The application is solidified the distance and position between adjacent three long purlins through long purlin detent mechanism 4; Be crimped on the locating notch 5 of long purlin detent mechanism 4 locating long purlin 2; Long purlin through long purlin compactor 7 compresses a little 6 and will locate long purlin 2 and compress, and longer purlin 3 to be positioned is fixed on the location of realization long purlin to be positioned on the corresponding locating point of long purlin detent mechanism 4.
See Fig. 3 and Fig. 4; The application's long purlin detent mechanism 4 is by containing long purlin compactor 7 and long purlin locating plate 8; On long purlin locating plate 8, be provided with a group leader purlin locating notch 5, by the distance and position that long purlin locating notch 5 solidifies between the adjacent long purlin, long purlin compactor 7 is common production-release designs; Long purlin compactor 7 preferably is fixed in the middle of one group of parallel long purlin locating plate 8, the long purlin on the compactor of long purlin compress a little 6 with long purlin locating plate 8 on 5 coincidences of long purlin locating notch consistent.
Claims (3)
1. the localization method of the long purlin of an aircraft; Relative position relation, a long purlin detent mechanism between known long purlin to be positioned and two the oriented long purlins; It is characterized in that; Be provided with a plurality of long purlins locating point in the detent mechanism of described long purlin; This length purlin locating point has solidified two relative position relations of having located long purlin and long purlin to be positioned, and two oriented long purlins are fixed on the corresponding locating point of long purlin detent mechanism, longer purlin to be positioned is fixed on the location of realizing long purlin to be positioned on the corresponding locating point of long purlin detent mechanism.
2. an aircraft is grown the purlin detent mechanism; It is characterized in that containing long purlin compactor and long purlin locating plate; Described long purlin locating plate is provided with a group leader purlin locating notch; Long purlin compactor is fixed on the locating plate of long purlin, the long purlin on the compactor of long purlin compress a little with length purlin locating plate on the positioning groove stomion coincidence of long purlin consistent.
3. like the long purlin of claims 1 described aircraft detent mechanism, it is characterized in that described long purlin compactor is fixed in the middle of one group of parallel long purlin locating plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210116673.4A CN102602546B (en) | 2012-04-19 | 2012-04-19 | Aircraft stringer positioning method and mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210116673.4A CN102602546B (en) | 2012-04-19 | 2012-04-19 | Aircraft stringer positioning method and mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102602546A true CN102602546A (en) | 2012-07-25 |
| CN102602546B CN102602546B (en) | 2014-07-09 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210116673.4A Active CN102602546B (en) | 2012-04-19 | 2012-04-19 | Aircraft stringer positioning method and mechanism |
Country Status (1)
| Country | Link |
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| CN (1) | CN102602546B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104002990A (en) * | 2014-06-06 | 2014-08-27 | 清华大学 | Fixed positioning device of front section part of aircraft product |
| CN108943776A (en) * | 2018-06-27 | 2018-12-07 | 西安飞机工业（集团）有限责任公司 | A kind of detachable is adjustable stringer clamping and positioning device and localization method |
| CN110682549A (en) * | 2019-10-09 | 2020-01-14 | 江西洪都航空工业集团有限责任公司 | Combined core mold tool for stiffened wall plate and forming process method thereof |
| CN111531495A (en) * | 2020-05-15 | 2020-08-14 | 沈阳飞机工业（集团）有限公司 | Method for controlling spacing of composite material T or I-shaped stringer |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4381104A (en) * | 1980-09-29 | 1983-04-26 | The Boeing Company | Stringer clamp |
| US7103985B1 (en) * | 2004-12-17 | 2006-09-12 | Roll Forming Corporation | Stringer check fixture and method |
| CN201205689Y (en) * | 2007-12-29 | 2009-03-11 | 成都飞机工业（集团）有限责任公司 | Movable fixture clamping positioning device |
| CN201423426Y (en) * | 2009-04-24 | 2010-03-17 | 东风设计研究院有限公司 | Riveting and totally assembling fixture of vehicle frame |
| CN201864042U (en) * | 2010-11-19 | 2011-06-15 | 陕西飞机工业（集团）有限公司 | Aircraft stringer assembly device |
-
2012
- 2012-04-19 CN CN201210116673.4A patent/CN102602546B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4381104A (en) * | 1980-09-29 | 1983-04-26 | The Boeing Company | Stringer clamp |
| US7103985B1 (en) * | 2004-12-17 | 2006-09-12 | Roll Forming Corporation | Stringer check fixture and method |
| CN201205689Y (en) * | 2007-12-29 | 2009-03-11 | 成都飞机工业（集团）有限责任公司 | Movable fixture clamping positioning device |
| CN201423426Y (en) * | 2009-04-24 | 2010-03-17 | 东风设计研究院有限公司 | Riveting and totally assembling fixture of vehicle frame |
| CN201864042U (en) * | 2010-11-19 | 2011-06-15 | 陕西飞机工业（集团）有限公司 | Aircraft stringer assembly device |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104002990A (en) * | 2014-06-06 | 2014-08-27 | 清华大学 | Fixed positioning device of front section part of aircraft product |
| CN104002990B (en) * | 2014-06-06 | 2016-04-27 | 清华大学 | The fixed type registration device of aircraft product leading portion parts |
| CN108943776A (en) * | 2018-06-27 | 2018-12-07 | 西安飞机工业（集团）有限责任公司 | A kind of detachable is adjustable stringer clamping and positioning device and localization method |
| CN108943776B (en) * | 2018-06-27 | 2020-06-09 | 西安飞机工业（集团）有限责任公司 | Detachable adjustable stringer clamping and positioning device and positioning method |
| CN110682549A (en) * | 2019-10-09 | 2020-01-14 | 江西洪都航空工业集团有限责任公司 | Combined core mold tool for stiffened wall plate and forming process method thereof |
| CN110682549B (en) * | 2019-10-09 | 2022-03-15 | 江西洪都航空工业集团有限责任公司 | Combined core mold tool for stiffened wall plate and forming process method thereof |
| CN111531495A (en) * | 2020-05-15 | 2020-08-14 | 沈阳飞机工业（集团）有限公司 | Method for controlling spacing of composite material T or I-shaped stringer |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102602546B (en) | 2014-07-09 |
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