CN102658378A - Drilling method for wall plate skin of airplane - Google Patents
Drilling method for wall plate skin of airplane Download PDFInfo
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- CN102658378A CN102658378A CN2012101602112A CN201210160211A CN102658378A CN 102658378 A CN102658378 A CN 102658378A CN 2012101602112 A CN2012101602112 A CN 2012101602112A CN 201210160211 A CN201210160211 A CN 201210160211A CN 102658378 A CN102658378 A CN 102658378A
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- covering
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- wallboard
- wallboard covering
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Abstract
The invention provides a drilling method aiming at a small-curvature wall plate skin of an airplane and a large-curvature extensible wall plate skin of the airplane. The drilling method comprises the following steps of: drawing a hole site diagram on a gelatin plate according to the hole site theoretical data of the wall plate skin, and then, positioning and covering the gelatin plate at the corresponding position of the wall plate skin, and making hole site marks on the wall plate skin through pit punching work to realize the drilling of the wall plate skin. By using the method, the problems of hole site precision, drilling efficiency and drilling cost can be effectively considered.
Description
Technical field
The present invention relates to a kind of aircraft manufacturing mounting technology field, be specially adapted to the boring method of wallboard covering in the aircraft assembling process.
Background technology
In the development and production process of aircraft product,, need on the wallboard covering, bore a large amount of guide holes in order to realize assembling.Owing to assembling needs or reason such as change in design, the position of these guide holes often needs adjustment in assembling process, therefore generally not in the part production process but in assembling process, drill through.It is thus clear that wallboard covering boring method is for improving the aircraft efficiency of assembling fast and accurately, the shortening aircraft development production cycle has great importance.
At present, for drilling quality and the efficient that improves the wallboard covering, technical equipment department need provide special boring mould.Drill jig commonly used mainly is machined profile drill jig and planar development boring model.Drill jig to manufacture and design the cycle long, manufacturing cost is high, volume is big, carrying is used inconvenient in the assembly shop.The rigidity of drill jig and wallboard covering is all bigger, and it is often not tight to fit during boring, influences drilling quality.When the position, position, hole on the covering is adjusted, need reprocess drill jig, under the serious situation even cause drill jig to scrap.In addition, the drill jig boring method is applicable to big batch Aircraft Production process, and for the Aircraft Production process of the small batch development process of new architecture particularly, it is less economical.
Under the situation that drill jig is not provided, often adopt manual line boring method at present, the operation easier of this method is bigger, and operator's physical demands is big, and efficient is low, and position, hole precision is difficult to guarantee.
Summary of the invention:
In order to overcome the deficiency of above-mentioned existing method, it is a kind of to the aircraft target ship covering of small curve and the boring method of the extensible aircraft target ship covering of deep camber that the present invention provides.This method can effectively be taken into account position, hole precision, drilling efficiency and boring cost problem.
A kind of boring method of aircraft target ship covering; The wallboard covering and the hole potential theory data of design on this wallboard covering that contain needs boring; It is characterized in that, on gelatin plate, draw the hole bitmap according to the hole potential theory data of above-mentioned wallboard covering, the gelatin plate location that will draw porose bitmap again covers on the correspondence position of wallboard covering; See through gelatin plate and on the wallboard covering, get position, hole mark towards operation, realize the boring of wallboard covering at last according to this position, hole mark through beating the ocean.
The invention has the beneficial effects as follows: give the boring of wallboard covering through adopting stroke gelatin plate that hole bitmap on the wallboard covering is arranged, it is long to have overcome the conventional molds boring method manufacturing cycle, the deficiency that cost is high; Compare with traditional boring mould, offset plate matter is soft, can fully fit with the wallboard covering during operation, helps guaranteeing the required precision of position, hole; Compare with manual line boring method, operation easier of the present invention is little, and efficient is high, and position, hole precision guarantees that easily operator's physical demands is little.When the position, hole on the wallboard covering need be adjusted, only need the cross wire at place, foramen primum position on the bitmap of hole to be wiped off with blade, draw again at the place in new position, hole, can not cause gelatin plate to scrap.
Below in conjunction with the embodiment accompanying drawing the application is described in further detail.
Description of drawings
Fig. 1 is the gelatin plate sketch map that the embodiment of the invention is drawn.
Fig. 2 is the wallboard covering sketch map before the embodiment of the invention boring.
Fig. 3 is an embodiment of the invention bore operation process sketch map.
Fig. 4 is an embodiment of the invention bore operation sketch map as a result.
Numbering explanation among the figure: 1 gelatin plate, position, 2 hole, 3 datum axis, 4 wallboard coverings, 5 adhesive tapes, 6 guide holes, 7 axes of aircrafts.
The specific embodiment
Below in conjunction with embodiment and accompanying drawing the present invention is further described.
The boring method of aircraft target ship covering provided by the invention is to utilize stroke gelatin plate that hole bitmap on the wallboard covering is arranged to carry out the method for bore operation for the wallboard covering, and this method may further comprise the steps:
1, draws stroke gelatin plate 1 that hole bitmap on the wallboard covering is arranged: as shown in Figure 1; According to the area invariance principle; By CATIA V5 software the theoretical profile of the digitlization of certain piece wallboard covering of certain model aircraft is launched; The panel data of the position, hole 2 on the acquisition wallboard covering and the position of datum axis 3, its mesopore position representes that with cross wire datum axis comprises long purlin line and axis; These data are input to the Kongsberg flat-bed plotter, draw the hole bitmap that constitutes by position, hole 2 and datum axis 3 at gelatin plate 1 with the Kongsberg flat-bed plotter.
2, based on positioning reference gelatin plate 1 is covered on the wallboard covering 4: with the axes of aircraft on the wallboard covering 47 is positioning reference; The datum axis 3 of gelatin plate is corresponding with axes of aircraft 7 positions on the wallboard covering 4; With adhesive tape 5 gelatin plate 1 is fixed on the wallboard covering 4; Gelatin plate and wallboard covering 4 are fully fitted, as shown in Figure 2.
3, adopt the ocean to dash the correspondence position of gelatin plate being moved to wallboard covering 4 based on the position, hole 2 on the positioning reference: the tip that the ocean is dashed is positioned at the center of position, hole 2 on the gelatin plate 1, wallboard covering 4 is beaten foreign towards operation.
4, gelatin plate is removed from wallboard covering 4, beat the ocean towards the some hole that operation produces, adopt the pneumatic drilling machine of hand held on wallboard covering 4, to hole according to step 3.
Through above step, on wallboard covering 4, bore and got well guide hole as shown in Figure 36.
State on the implementation in the process of step 2, can fully fit in order to make gelatin plate 1 and wallboard covering 4, the position gap that can on gelatin plate 1, have nothing to do with position, hole 2, gelatin plate 1 is further fixing in indentation, there with adhesive tape 5; In order to improve drilling accuracy, during the gelatin plate 1 of location, choose as far as possible with assemble the aircraft process in the consistent positioning reference of location wallboard covering 4.
The storage environment that it is pointed out that gelatin plate commonly used at last is 16～24 degrees centigrade of temperature, humidity 40%～60%.Offset plate is not placed under the environment that does not satisfy above-mentioned condition for a long time,, influences borehole accuracy in order to avoid cause the offset plate distortion.
Claims (1)
1. the boring method of an aircraft target ship covering; The wallboard covering and the hole potential theory data of design on this wallboard covering that contain needs boring; It is characterized in that, on gelatin plate, draw the hole bitmap according to the hole potential theory data of above-mentioned wallboard covering, the gelatin plate location that will draw porose bitmap again covers on the correspondence position of wallboard covering; See through gelatin plate and on the wallboard covering, get position, hole mark towards operation, realize the boring of wallboard covering at last according to this position, hole mark through beating the ocean.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012101602112A CN102658378A (en) | 2012-05-22 | 2012-05-22 | Drilling method for wall plate skin of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012101602112A CN102658378A (en) | 2012-05-22 | 2012-05-22 | Drilling method for wall plate skin of airplane |
Publications (1)
| Publication Number | Publication Date |
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| CN102658378A true CN102658378A (en) | 2012-09-12 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN2012101602112A Pending CN102658378A (en) | 2012-05-22 | 2012-05-22 | Drilling method for wall plate skin of airplane |
Country Status (1)
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Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103286767A (en) * | 2013-06-13 | 2013-09-11 | 沈阳飞机工业（集团）有限公司 | Drilling lineation method for skin part |
| CN103785875A (en) * | 2014-01-06 | 2014-05-14 | 江苏通达动力科技股份有限公司 | Drilling method for drilling auxiliary device |
| CN105268902A (en) * | 2015-11-17 | 2016-01-27 | 江西洪都航空工业集团有限责任公司 | Closed interval rivet hole manufacturing alignment device |
| CN106346050A (en) * | 2015-07-17 | 2017-01-25 | 成都飞机工业（集团）有限责任公司 | Method for relocation of hole site |
| CN106985404A (en) * | 2017-04-21 | 2017-07-28 | 陕西飞机工业（集团）有限公司 | A kind of composite cellular board and composite cellular board connection method |
| CN109604504A (en) * | 2018-11-30 | 2019-04-12 | 四川航天长征装备制造有限公司 | A kind of minor diameter, taper section mounted inside Quick-rivet and detection method |
| CN110217405A (en) * | 2019-05-17 | 2019-09-10 | 陕西飞机工业（集团）有限公司 | A kind of aircraft delivery device installation method |
| CN110309568A (en) * | 2019-06-21 | 2019-10-08 | 江西洪都航空工业集团有限责任公司 | Decussation line creation method based on CATIA |
| CN110355819A (en) * | 2019-06-18 | 2019-10-22 | 成都飞机工业（集团）有限责任公司 | A kind of method for drilling of covering and skeleton connection structure |
| CN111168324A (en) * | 2020-03-16 | 2020-05-19 | 沈阳飞机工业（集团）有限公司 | Drilling method for AF1410 steel part after quenching |
| CN111230424A (en) * | 2020-03-16 | 2020-06-05 | 沈阳飞机工业（集团）有限公司 | Method for unifying machining references among various working procedures of large skin |
| CN112935349A (en) * | 2019-12-10 | 2021-06-11 | 中航贵州飞机有限责任公司 | Method for machining accurate lead hole on skin of training machine |
| CN113118493A (en) * | 2020-01-15 | 2021-07-16 | 中国商用飞机有限责任公司 | Skin opening device and process method |
| CN113369530A (en) * | 2021-06-23 | 2021-09-10 | 成都飞机工业（集团）有限责任公司 | Device for making holes in aircraft skin and using method thereof |
| CN113459199A (en) * | 2021-06-24 | 2021-10-01 | 成都飞机工业（集团）有限责任公司 | Hole making method for porous similar skin part |
| CN114719727A (en) * | 2022-03-25 | 2022-07-08 | 四川腾盾科技有限公司 | Method for assembling, positioning and detecting aircraft finished product based on magnet heteropolar attraction |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050084344A1 (en) * | 2003-10-20 | 2005-04-21 | The Boeing Company | Drill template with integral vacuum attach |
| CN200999095Y (en) * | 2007-01-30 | 2008-01-02 | 谭水柱 | Local expansion sample plate for airplane production |
| CN201244628Y (en) * | 2008-08-22 | 2009-05-27 | 成都飞机工业（集团）有限责任公司 | Rapid hole-guiding device for covering |
| CN102240824A (en) * | 2011-05-11 | 2011-11-16 | 西安飞机工业（集团）有限责任公司 | Wall panel skin shape drilling die and manufacturing method thereof |
-
2012
- 2012-05-22 CN CN2012101602112A patent/CN102658378A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050084344A1 (en) * | 2003-10-20 | 2005-04-21 | The Boeing Company | Drill template with integral vacuum attach |
| CN200999095Y (en) * | 2007-01-30 | 2008-01-02 | 谭水柱 | Local expansion sample plate for airplane production |
| CN201244628Y (en) * | 2008-08-22 | 2009-05-27 | 成都飞机工业（集团）有限责任公司 | Rapid hole-guiding device for covering |
| CN102240824A (en) * | 2011-05-11 | 2011-11-16 | 西安飞机工业（集团）有限责任公司 | Wall panel skin shape drilling die and manufacturing method thereof |
Cited By (23)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103286767A (en) * | 2013-06-13 | 2013-09-11 | 沈阳飞机工业（集团）有限公司 | Drilling lineation method for skin part |
| CN103286767B (en) * | 2013-06-13 | 2015-09-09 | 沈阳飞机工业（集团）有限公司 | A kind of layout for drilling method of skin part |
| CN103785875A (en) * | 2014-01-06 | 2014-05-14 | 江苏通达动力科技股份有限公司 | Drilling method for drilling auxiliary device |
| CN106346050A (en) * | 2015-07-17 | 2017-01-25 | 成都飞机工业（集团）有限责任公司 | Method for relocation of hole site |
| CN105268902A (en) * | 2015-11-17 | 2016-01-27 | 江西洪都航空工业集团有限责任公司 | Closed interval rivet hole manufacturing alignment device |
| CN106985404A (en) * | 2017-04-21 | 2017-07-28 | 陕西飞机工业（集团）有限公司 | A kind of composite cellular board and composite cellular board connection method |
| CN109604504A (en) * | 2018-11-30 | 2019-04-12 | 四川航天长征装备制造有限公司 | A kind of minor diameter, taper section mounted inside Quick-rivet and detection method |
| CN109604504B (en) * | 2018-11-30 | 2021-03-23 | 四川航天长征装备制造有限公司 | Method for quickly riveting and detecting small-diameter and tapered section internal assembly |
| CN110217405A (en) * | 2019-05-17 | 2019-09-10 | 陕西飞机工业（集团）有限公司 | A kind of aircraft delivery device installation method |
| CN110355819A (en) * | 2019-06-18 | 2019-10-22 | 成都飞机工业（集团）有限责任公司 | A kind of method for drilling of covering and skeleton connection structure |
| CN110355819B (en) * | 2019-06-18 | 2021-11-30 | 成都飞机工业（集团）有限责任公司 | Hole making method for skin and skeleton connecting structure |
| CN110309568A (en) * | 2019-06-21 | 2019-10-08 | 江西洪都航空工业集团有限责任公司 | Decussation line creation method based on CATIA |
| CN110309568B (en) * | 2019-06-21 | 2022-07-08 | 江西洪都航空工业集团有限责任公司 | Cross cross line creating method based on CATIA |
| CN112935349B (en) * | 2019-12-10 | 2022-12-09 | 中航贵州飞机有限责任公司 | Method for machining accurate lead hole on skin of training machine |
| CN112935349A (en) * | 2019-12-10 | 2021-06-11 | 中航贵州飞机有限责任公司 | Method for machining accurate lead hole on skin of training machine |
| CN113118493A (en) * | 2020-01-15 | 2021-07-16 | 中国商用飞机有限责任公司 | Skin opening device and process method |
| CN113118493B (en) * | 2020-01-15 | 2022-07-12 | 中国商用飞机有限责任公司 | Skin opening device and process method |
| CN111168324B (en) * | 2020-03-16 | 2021-07-09 | 沈阳飞机工业（集团）有限公司 | Drilling method for AF1410 steel part after quenching |
| CN111230424A (en) * | 2020-03-16 | 2020-06-05 | 沈阳飞机工业（集团）有限公司 | Method for unifying machining references among various working procedures of large skin |
| CN111168324A (en) * | 2020-03-16 | 2020-05-19 | 沈阳飞机工业（集团）有限公司 | Drilling method for AF1410 steel part after quenching |
| CN113369530A (en) * | 2021-06-23 | 2021-09-10 | 成都飞机工业（集团）有限责任公司 | Device for making holes in aircraft skin and using method thereof |
| CN113459199A (en) * | 2021-06-24 | 2021-10-01 | 成都飞机工业（集团）有限责任公司 | Hole making method for porous similar skin part |
| CN114719727A (en) * | 2022-03-25 | 2022-07-08 | 四川腾盾科技有限公司 | Method for assembling, positioning and detecting aircraft finished product based on magnet heteropolar attraction |
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Application publication date: 20120912 |