CN201864042U - Aircraft stringer assembly device - Google Patents
Aircraft stringer assembly device Download PDFInfo
- Publication number
- CN201864042U CN201864042U CN2010206199463U CN201020619946U CN201864042U CN 201864042 U CN201864042 U CN 201864042U CN 2010206199463 U CN2010206199463 U CN 2010206199463U CN 201020619946 U CN201020619946 U CN 201020619946U CN 201864042 U CN201864042 U CN 201864042U
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- China
- Prior art keywords
- draw runner
- slide
- long purlin
- screw
- aircraft
- 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.)
- Expired - Fee Related
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Abstract
The utility model belongs to a device for positioning and clamping a stringer in the field of aircraft assembly, which relates to a stringer positioning and clamping device. An aircraft stringer assembly device comprises a draw runner, a sliding seat, a concave snap-gauge, a lock screw and a compression screw, wherein the sliding seat is fit and fixed on the concave snap-gauge; the faying surface of the sliding seat is provided with a rectangular chute for placing the draw runner; the sliding seat is provided with a threaded hole used for the lock screw to be screwed in to lock the draw runner; the main body of the draw runner is a rectangular thin block; a boss is vertically welded at the side front end of the rectangular thin block; the boss is provided with the threaded hole for the compression screw to be screwed in; and part of the main body of the draw runner is arranged in the rectangular chute on the sliding seat. By adopting the device, the problem that positioning the angle of strike of the stringer on the molded surface of the concave snap-gauge wastes time and labor, the repair problem in the product trial assembly process, the problem that components are difficult to remove from shelves and the problem that a convex oblique angle needs to be considered in design and manufacture are solved. The device is mainly used for positioning and clamping the stringer of aircraft panel components with higher dual curvatures.
Description
Technical field
The utility model belongs to the device of locating and clamp long purlin in the aircraft assembling field, relates to a kind of location, long purlin and fixing device.
Background technology
The long purlin of aircraft assembling device is a kind of production tooling that is used for locating and clamping long purlin in the aircraft fitting process.Whether the deft design of the long purlin assembling of aircraft auxiliary device directly has influence on the assembly quality and the efficiency of assembling of aircraft.
The aircraft assembling must just can be carried out by the long purlin of frock aircraft assembling device.Widespread location and clamping form as shown in Figure 1 in the present industry, its operating process is: will grow on the locating surface that purlin 10 is put in supporting plate 14, rotate hook 11 directions and screw knurled nut 13 simultaneously, make hook hook long purlin 10, thereby realize the location and the clamping of long purlin.The long purlin that this form needs the workman to provide according to the loft model is moved towards the angle value and is frustrated on interior shape clamp locating surface and repair angle, and the locating surface on every clamp can not guarantee in full accordly, therefore, may produce a large amount of reclamation works in product trial assembly process; Efficiency of assembling is low; Parts undercarriage inconvenience; For the big parts of hyperbolic degree, fixing device must be considered the profile bevel angle value, therefore, the design that hooks seat and the position of hook be provided with require highly, and manufacture difficulty is big.
Summary of the invention
The utility model purpose is: provide that a kind of manufacturing assembly difficulty is low, the undercarriage long purlin of aircraft assembling device easily.
The technical solution of the utility model is: the long purlin of a kind of aircraft assembling device, and it comprises draw runner, slide; Interior shape clamp; Lock screw, housing screw, wherein, slide fit be fixed on interior shape clamp on, have one to be used to place the rectangle chute of draw runner on its binding face, and have on the slide and be used for the tapped bore that lock screw screws in the locking draw runner, described draw runner main body is the thin piece of rectangle, its side front end vertical welding is connected to a boss, and is provided with the tapped bore that the tight screw of voltage supply screws on boss, and described draw runner base portion is arranged in the rectangle chute on the slide.
Described housing screw is by the boss on the screw-in of the kidney slot on the two-sided briquetting draw runner.
Described slide is a few font squares, and its two-end thickness is less than the thickness at middle chute place.
Described slide is located by tommy, and is clamped on the interior shape clamp by screw bolt and nut.
Rectangle chute width and draw runner width basically identical on the described slide are bearing fit between the two.The beneficial effects of the utility model are: the long purlin of the utility model aircraft assembling device is only left long purlin by breach on the interior type clamp in operating process, does not need to carry out angle and frustrates and repair, and makes and difficulty is joined in trial assembly thereby effectively reduce.And, need not consider long purlin axial angle, thereby obtain higher assembly precision easily because the draw runner on the long purlin is thinner.In addition by unclamping lock screw, can mobile easily draw runner, the draw runner locating surface is withdrawed from bottom surface, long purlin, thereby make that the operation of product undercarriage is comparatively convenient.Flexible by draw runner can be adjusted the distance between draw runner and the long purlin profile, thereby under curvature changes greatly situation, also do not need to consider the profile bevel angle value, so can reduce design difficulty and manufacture difficulty.
Description of drawings
Fig. 1 is the long purlin assembling of an a kind of prior art aircraft scheme drawing;
Fig. 2 is the structural representation of the long purlin of the utility model aircraft assembling device;
Fig. 3 is the structural representation of slide among Fig. 2;
Fig. 4 is the structural representation of draw runner among Fig. 2,
Among the figure: draw runner 1, slide 2, interior shape clamp 3, bolt 4, nut 5, lock screw 6, tommy 7, two-sided briquetting 8, housing screw 9, long purlin 10, hook 11, hook seat 12, knurled nut 13, supporting plate 14.
The specific embodiment
See also Fig. 2, it is the structural representation of the long purlin of the utility model aircraft assembling device.In the present embodiment, the long purlin of described aircraft assembling device comprises draw runner 1, slide 2, interior shape clamp 3, bolt 4, nut 5, lock screw 6, locating dowel pin 7, two-sided briquetting 8, housing screw 9.
Wherein, Fig. 3 is the structural representation of slide among Fig. 2, and slide 2 is a few font squares, and has on interior shape clamp 3 binding faces and the draw runner 1 wide rectangle chute that is used to place draw runner 1.Be pressed into four circular holes that pass through with bolt 4 with being useful on tommy 7 on interior shape clamp 3 binding faces, its position is symmetrically distributed, and slide 2 is clamped on the interior shape clamp 3 by bolt 4 and nut 5 by tommy 7 location.Have one on the slide 2 and be used for the tapped bore that lock screw 6 screws in locking draw runner 1.
See also Fig. 4, Fig. 4 is the structural representation of draw runner among Fig. 2, and described draw runner 1 base portion is the thin piece of rectangle, and thickness is less than 5mm, and its side front end vertical welding is connected to a boss, and makes the tapped bore that the tight screw 9 of voltage supply screws on boss.Draw runner 1 base portion is fixed in the rectangle chute on the slide 2.
During actual the use, long purlin is put in interior shape clamp gap position.Unclamp the lock screw 6 on the slide, regulate the length of draw runner 1 on the aircraft length purlin assembling auxiliary device, guarantee that the draw runner head surpasses 2/3 position of long purlin locating surface, locked lock screw 6, thus realization is to the location of long purlin.
Unclamp the housing screw 9 on the draw runner then, adjust the position of two-sided briquetting 8, guarantee that 8 one of two-sided briquettings are pressed on the long purlin, the other end is pressed on the boss of draw runner 1, and screws housing screw 9, thereby realizes that long purlin is fixed.
During undercarriage, unclamp the housing screw 9 on the draw runner 1 earlier, two-sided briquetting 8 is screwed out, unclamp long purlin, unclamp the lock screw 6 on the slide 2 then, the projection section that the operator can spur on the draw runner 1 moves along the chute direction of slide 2, thereby realizes the flexible of draw runner 1.Therefore can make draw runner 1 locating surface withdraw from bottom surface, long purlin, with aspect product undercarriage.
The long purlin of the utility model aircraft assembling device passes through the clamping of the cooperation realization of housing screw 9 and two-sided briquetting 8 to long purlin, compresses the location that draw runner is realized long purlin by lock screw.In operating process, only leave long purlin on the interior type clamp by breach, do not need to carry out angle and frustrate and repair, join difficulty thereby effectively reduce manufacturing and trial assembly, simultaneously, because the draw runner on the long purlin is thinner, need not consider long purlin axial angle, thereby obtain higher assembly precision easily.And because by unclamping lock screw, can mobile easily draw runner, the draw runner locating surface is withdrawed from bottom surface, long purlin, thereby make that the operation of product undercarriage is comparatively convenient.Flexible by draw runner can be adjusted the distance between draw runner and the long purlin profile, thereby under curvature changes greatly situation, also do not need to consider the profile bevel angle value, so can reduce design difficulty and manufacture difficulty.
At first, mill out interior shape clamp profile, on clamp, launch long purlin axis then or, carve long purlin axis, only need on the clamp to leave, pass through for long purlin than the big breach in outside, long purlin by shape clamp in the numerical control manufacturing by model by traditional process; On the shape clamp, the draw runner locating surface is consistent with long purlin axis in then the long purlin assembling of aircraft auxiliary device being installed in.The installation site of slide determines by draw runner, the draw runner head on interior shape clamp profile, draw runner breech face and slide end face; Draw runner on the long purlin assembling of the aircraft auxiliary device can be free to slide in the chute of slide, adjust to back screw by housing screw locked; After long purlin is placed on the draw runner locating surface, unclamp the housing screw on the draw runner boss, adjust two-sided briquetting, the one head is pressed onto on the long purlin, on the other boss face that is pressed in draw runner, and then screws housing screw, long purlin is fixed, thereby realized location and clamping long purlin.
Claims (5)
1. an aircraft is grown the purlin assembling device, it is characterized in that: comprise draw runner (1), slide (2), interior shape clamp (3), lock screw (6), housing screw (9), wherein, slide (2) fit be fixed on interior shape clamp (3) on, have one to be used to place the rectangle chute of draw runner (1) on its binding face, and have on the slide (2) and be used for the tapped bore that lock screw (6) screws in locking draw runner (1), described draw runner (1) main body is the thin piece of rectangle, its side front end vertical welding is connected to a boss, and is provided with the tapped bore that the tight screw of voltage supply (9) screws on boss, and described draw runner (1) base portion is arranged in the rectangle chute on the slide (2).
2. the long purlin of aircraft according to claim 1 assembling device is characterized in that: described housing screw (9) is by in the boss on the screw-in draw runner of the kidney slot on the two-sided briquetting (8) (1).
3. the long purlin of aircraft according to claim 2 assembling device, it is characterized in that: described slide (2) is a few font squares, and its two-end thickness is less than the thickness at middle chute place.
4. the long purlin of aircraft according to claim 3 assembling device, it is characterized in that: described slide is located by tommy (7), and is clamped on the interior shape clamp (3) by bolt (4) and nut (5).
5. the long purlin of aircraft according to claim 4 assembling device, it is characterized in that: rectangle chute width and draw runner width basically identical are bearing fit between the two.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010206199463U CN201864042U (en) | 2010-11-19 | 2010-11-19 | Aircraft stringer assembly device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010206199463U CN201864042U (en) | 2010-11-19 | 2010-11-19 | Aircraft stringer assembly device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201864042U true CN201864042U (en) | 2011-06-15 |
Family
ID=44135204
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010206199463U Expired - Fee Related CN201864042U (en) | 2010-11-19 | 2010-11-19 | Aircraft stringer assembly device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201864042U (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102554827A (en) * | 2011-12-28 | 2012-07-11 | 西北工业大学 | Positioning and clamping device used for assembling front flap in airplane |
| CN102554826A (en) * | 2011-12-28 | 2012-07-11 | 西北工业大学 | Positioning and clamping device |
| CN102602546A (en) * | 2012-04-19 | 2012-07-25 | 西安飞机工业（集团）有限责任公司 | Aircraft stringer positioning method and mechanism |
| CN102601752A (en) * | 2012-04-19 | 2012-07-25 | 西安飞机工业（集团）有限责任公司 | Aircraft wing wall panel butt joint stringer locating device |
| CN105666377A (en) * | 2014-11-17 | 2016-06-15 | 昌河飞机工业（集团）有限责任公司 | Positioning clamp used for assembly of rear-section piece during gluing assembly of paddle |
| 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 |
| CN109367812A (en) * | 2018-11-07 | 2019-02-22 | 昌河飞机工业（集团）有限责任公司 | A kind of compressing structure |
| CN109605103A (en) * | 2018-12-13 | 2019-04-12 | 上海航天设备制造总厂有限公司 | A kind of device for the bilateral positioning of cornual plate |
| CN110125848A (en) * | 2019-05-16 | 2019-08-16 | 沈阳飞机工业（集团）有限公司 | A kind of quick stringer part locator and its application method |
| CN112093074A (en) * | 2020-09-04 | 2020-12-18 | 江西昌河航空工业有限公司 | Stringer positioning and pressing device with pressing plates |
-
2010
- 2010-11-19 CN CN2010206199463U patent/CN201864042U/en not_active Expired - Fee Related
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102554826B (en) * | 2011-12-28 | 2014-03-12 | 西北工业大学 | Positioning and clamping device |
| CN102554826A (en) * | 2011-12-28 | 2012-07-11 | 西北工业大学 | Positioning and clamping device |
| CN102554827A (en) * | 2011-12-28 | 2012-07-11 | 西北工业大学 | Positioning and clamping device used for assembling front flap in airplane |
| CN102554827B (en) * | 2011-12-28 | 2014-03-12 | 西北工业大学 | Positioning and clamping device used for assembling front flap in airplane |
| CN102602546B (en) * | 2012-04-19 | 2014-07-09 | 西安飞机工业（集团）有限责任公司 | Aircraft stringer positioning method and mechanism |
| CN102601752A (en) * | 2012-04-19 | 2012-07-25 | 西安飞机工业（集团）有限责任公司 | Aircraft wing wall panel butt joint stringer locating device |
| CN102602546A (en) * | 2012-04-19 | 2012-07-25 | 西安飞机工业（集团）有限责任公司 | Aircraft stringer positioning method and mechanism |
| CN105666377A (en) * | 2014-11-17 | 2016-06-15 | 昌河飞机工业（集团）有限责任公司 | Positioning clamp used for assembly of rear-section piece during gluing assembly of paddle |
| 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 |
| CN109367812A (en) * | 2018-11-07 | 2019-02-22 | 昌河飞机工业（集团）有限责任公司 | A kind of compressing structure |
| CN109605103A (en) * | 2018-12-13 | 2019-04-12 | 上海航天设备制造总厂有限公司 | A kind of device for the bilateral positioning of cornual plate |
| CN110125848A (en) * | 2019-05-16 | 2019-08-16 | 沈阳飞机工业（集团）有限公司 | A kind of quick stringer part locator and its application method |
| CN112093074A (en) * | 2020-09-04 | 2020-12-18 | 江西昌河航空工业有限公司 | Stringer positioning and pressing device with pressing plates |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110615 Termination date: 20181119 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |