CN105710270A - Process for eliminating riveting gap of thin aircraft web - Google Patents
Process for eliminating riveting gap of thin aircraft web Download PDFInfo
- Publication number
- CN105710270A CN105710270A CN201610202981.7A CN201610202981A CN105710270A CN 105710270 A CN105710270 A CN 105710270A CN 201610202981 A CN201610202981 A CN 201610202981A CN 105710270 A CN105710270 A CN 105710270A
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- CN
- China
- Prior art keywords
- thin web
- web plate
- angle
- angle stiffener
- stiffener
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J15/00—Riveting
- B21J15/02—Riveting procedures
Abstract
The invention provides a process for eliminating a riveting gap of a thin aircraft web. An L-shaped closed inclined angle material is bonded on the back surface of the thin web as a reinforced angle material; a fastening part through hole is formed in the reinforced angle material for positioning the thin web and the reinforced angle material; and during riveting, the reinforced angle material is tightly fixed on the thin web by using a fastening part, and is fixed with other parts. The process is simple in structure and high in adaptability, reduces the riveting deformation through reinforcing the thin web parts, effectively solves the agitation of the web and the generation of gaps, improves the machining efficiency, reduces the generation of operation faults, and reduces the rejection rate.
Description
Technical field
The application relates to aircraft assembling manufacturing manufacture field, particularly a kind of processing technique eliminating aircraft thin web plate riveted joint gap.
Background technology
In aircraft manufacturing field, aircraft assembling is the key link of aircraft manufacturing, its workload accounts for the 40%～50% of the whole aircraft manufacturing amount of labour, automation equipment is progressively used in aircraft riveted joint assembling, to meet higher performance, cannot the arriving the manual rivet quality at position simultaneously for automatic equipment and it is also proposed higher requirement of prescription.
Aircraft assembling manual rivet deflection is big, is the position closing oblique angle for Shi Mao district, owing to the restriction in space is easier to cause the generation of assembly failure.After sheet metal part angle section and thin web plate (thickness only has 0.63mm) assembling, owing to uneven and tolerance build-up, assembling defect, the part deformation etc. of surface stress distribution all can make to produce between part gap and easily cause and agitate phenomenon, this phenomenon can accelerate part fatigue, agitates so the method adjusted or compensate for must be taked to eliminate and rivets gap.
Summary of the invention
This application provides a kind of process eliminating aircraft thin web plate riveted joint gap.
1, a kind of process eliminating aircraft thin web plate riveted joint gap, comprises the following steps:
1) it is fitted in the thin web plate back side as angle stiffener with the oblique angle angle section that closes of L-type；
2) repair by different thin web plate profiles and cut angle stiffener length direction profile；
3) on angle stiffener, securing member is made by hole, for the location of thin web plate Yu angle stiffener；
4) surface that finishing polishing angle stiffener fits with thin web plate, makes angle stiffener thickness less than the minimum constructive height of heading after securing member molding；
5) on angle stiffener and thin web plate fit surface, adhesive tape, the surface of protection thin web plate are sticked；
6) repair cut not with thin web plate laminating angle stiffener another side, it is prevented that top the ferrum generation to part knock damage；
7) with securing member, angle stiffener it is tightly fixed on thin web plate and fixes with other parts during riveted joint.
It is an advantage of the current invention that simple in construction, the suitability is strong, by the reinforcement to thin web plate part, decreases rivet deformation.The method efficiently solve web agitate, the generation in gap, solve the generation closing the not open area knock damage such as oblique angle, it is ensured that product riveting quality simultaneously.Reduce and do over again the time, improve working (machining) efficiency, decrease the generation of operating trouble, reduce percent defective.
Below in conjunction with embodiment accompanying drawing, this application is described in further detail.
Accompanying drawing explanation
Fig. 1 angle stiffener duty is illustrated
Fig. 2 is the detail drawing of 1 in Fig. 1
Number description: 1 angle stiffener, 2 thin web plates, 3 sheet metal part angle sections, 4 securing members, 5 webs
Detailed description of the invention
Referring to accompanying drawing, a kind of process eliminating aircraft thin web plate riveted joint gap, completed by following steps:
1) it is fitted in thin web plate 2 back side as angle stiffener 1 with the oblique angle angle section that closes of L-type；
2) repair by different thin web plate 2 profiles and cut angle stiffener 1 length direction profile；
3) on angle stiffener 1, securing member 4 is made by hole, for the location of thin web plate 2 with angle stiffener 1；
4) surface that finishing polishing angle stiffener 1 fits with thin web plate 2, makes angle stiffener 1 thickness less than the minimum constructive height of heading after securing member 4 molding；
5) on angle stiffener 1 and thin web plate 2 fit surface, adhesive tape, the surface of protection thin web plate 2 are sticked；
6) repair cut not with thin web plate 2 laminating angle stiffener 1 another side, it is prevented that top the ferrum generation to part knock damage；
7) with securing member 4, angle stiffener 1 it is tightly fixed on thin web plate 2 and fixes with other parts during riveted joint.
Work process: first whole hole is made in the hole in securing member 4 installation site, before riveted joint, angle stiffener 1 is fixed on thin web plate 2 side, riveted joint correspondingly increases the intensity of thin web plate 2, completely eliminate the riveted joint gap between thin web plate 2 and sheet metal part angle section 3 and the generation agitated of thin web plate 2, decrease rivet deformation.Effectively prevent the generation riveting knock damage on web 5 simultaneously.
By on-the-spot utilization, the method efficiently solve web agitate, the generation in gap, it is ensured that product riveting quality.
Claims (1)
1. the process eliminating aircraft thin web plate riveted joint gap, it is characterised in that following steps:
1) it is fitted in the thin web plate back side as angle stiffener with the oblique angle angle section that closes of L-type；
2) repair by different thin web plate profiles and cut angle stiffener length direction profile；
3) on angle stiffener, securing member is made by hole, for the location of thin web plate Yu angle stiffener；
4) surface that finishing polishing angle stiffener fits with thin web plate, makes angle stiffener thickness less than the minimum constructive height of heading after securing member molding；
5) on angle stiffener and thin web plate fit surface, adhesive tape, the surface of protection thin web plate are sticked；
6) repair cut not with thin web plate laminating angle stiffener another side, it is prevented that top the ferrum generation to part knock damage；
7) with securing member, angle stiffener it is tightly fixed on thin web plate and fixes with other parts during riveted joint.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610202981.7A CN105710270B (en) | 2016-04-01 | 2016-04-01 | A kind of process for eliminating aircraft thin web plate riveting gap |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610202981.7A CN105710270B (en) | 2016-04-01 | 2016-04-01 | A kind of process for eliminating aircraft thin web plate riveting gap |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105710270A true CN105710270A (en) | 2016-06-29 |
| CN105710270B CN105710270B (en) | 2018-03-02 |
Family
ID=56160716
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610202981.7A Active CN105710270B (en) | 2016-04-01 | 2016-04-01 | A kind of process for eliminating aircraft thin web plate riveting gap |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105710270B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108145428A (en) * | 2016-11-23 | 2018-06-12 | 哈尔滨飞机工业集团有限责任公司 | A kind of large titanium alloy sheet assembly assembly technique |
| CN115107297A (en) * | 2022-06-29 | 2022-09-27 | 中航西安飞机工业集团股份有限公司 | Profile compensation control method for composite material T-shaped part |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1754318A1 (en) * | 1990-08-01 | 1992-08-15 | Самарский филиал Научно-исследовательского института технологии и организации производства двигателей | Method of demounting riveted joints |
| JP2008126793A (en) * | 2006-11-20 | 2008-06-05 | Honda Motor Co Ltd | Level difference adjustment structure for leading edge skin, and leading edge skin assembling method |
| CN201960376U (en) * | 2010-12-28 | 2011-09-07 | 江西昌河航空工业有限公司 | Tool for processing and positioning lamellar part |
| CN202244075U (en) * | 2011-06-03 | 2012-05-30 | 哈尔滨飞机工业集团有限责任公司 | Frame and wallboard connecting structure |
| CN104816837A (en) * | 2015-05-07 | 2015-08-05 | 哈尔滨飞机工业集团有限责任公司 | Aluminum alloy skin digital assembly method |
-
2016
- 2016-04-01 CN CN201610202981.7A patent/CN105710270B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1754318A1 (en) * | 1990-08-01 | 1992-08-15 | Самарский филиал Научно-исследовательского института технологии и организации производства двигателей | Method of demounting riveted joints |
| JP2008126793A (en) * | 2006-11-20 | 2008-06-05 | Honda Motor Co Ltd | Level difference adjustment structure for leading edge skin, and leading edge skin assembling method |
| CN201960376U (en) * | 2010-12-28 | 2011-09-07 | 江西昌河航空工业有限公司 | Tool for processing and positioning lamellar part |
| CN202244075U (en) * | 2011-06-03 | 2012-05-30 | 哈尔滨飞机工业集团有限责任公司 | Frame and wallboard connecting structure |
| CN104816837A (en) * | 2015-05-07 | 2015-08-05 | 哈尔滨飞机工业集团有限责任公司 | Aluminum alloy skin digital assembly method |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108145428A (en) * | 2016-11-23 | 2018-06-12 | 哈尔滨飞机工业集团有限责任公司 | A kind of large titanium alloy sheet assembly assembly technique |
| CN115107297A (en) * | 2022-06-29 | 2022-09-27 | 中航西安飞机工业集团股份有限公司 | Profile compensation control method for composite material T-shaped part |
| CN115107297B (en) * | 2022-06-29 | 2023-08-04 | 中航西安飞机工业集团股份有限公司 | Profile compensation control method for composite material T-shaped part |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105710270B (en) | 2018-03-02 |
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Address after: No. 710089 in Shaanxi province Xi'an city Yanliang District West Avenue Patentee after: AVIC Xi'an Aircraft Industry Group Co.,Ltd. Address before: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee before: AVIC AIRCRAFT Corp. |
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| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20210617 Address after: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee after: AVIC AIRCRAFT Corp. Address before: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee before: XI'AN AIRCRAFT BRANCH OF XI'AN AIRCRAFT INTERNATIONAL Corp. |