CN204725061U - A kind of weld jig of aircraft flap rail structure part electron-bombardment welding - Google Patents
A kind of weld jig of aircraft flap rail structure part electron-bombardment welding Download PDFInfo
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- CN204725061U CN204725061U CN201520373004.4U CN201520373004U CN204725061U CN 204725061 U CN204725061 U CN 204725061U CN 201520373004 U CN201520373004 U CN 201520373004U CN 204725061 U CN204725061 U CN 204725061U
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- abdominal cavity
- sliding track
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- web
- track body
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Abstract
A kind of weld jig of aircraft flap rail structure part electron-bombardment welding, this structural member comprise one have the sliding track body in multiple abdominal cavity and polylith corresponding with abdominal cavity needs welding web, the body of this fixture is a flat rigid structure, body is provided with multiple be located by connecting hole corresponding with sliding track body profile, locating piece and multiple fenestra corresponding with sliding track body abdominal cavity, the border of this fenestra is greater than the border in corresponding sliding track body abdominal cavity, the connector of a shaft-like is respectively provided with in the middle part of the two ends of body, two legs are separately had to be positioned at the two ends of body, the top of leg is auricle groove, fix with latch in the auricle groove that this connector is supported on leg top, two ends respectively.
Description
Technical field
The application relates to the electron beam welding field of aeronautical manufacture, specifically a kind of weld jig of aircraft flap rail structure part electron-bombardment welding.
Background technology
Aircraft flap rail structure part is for wing flap relative motion main inside and outside aircraft, promote or reduce the structural member of airfoil lift, the material of this slide rail is unimach, in order to alleviate the weight of component itself and increase the rigidity of structure, empty in sliding track body middle part and form multiple abdominal cavity, then embed web on the two sides in abdominal cavity and be welded.
Because the rigidity of structural member own is strong, in addition complex-shaped, have again adjacent multiple cavity both sides to need to weld thin web, welding position is more, and continuous weld is longer, and cause welding difficulty large, welding deformation is difficult to control.Especially the distortion of guide pass can not more than 0.3mm, so welding process is once cause large welding deformation, subsequent fine processing cannot ensure the wall thickness requirement of component, in addition, the weld seam in slide track component is enclosed type weld seam, although web is embedded in body, but welding process is unavoidable causes web to become arch or one jiao of tilting because of being heated uneven, and between electron beam welding characteristic, middle web also cannot be fixed by clamp body, is also one of problem.
So need to use suitable weld jig location to ensure that the relative position of structural member profile immobilizes, control welding deformation is the technological difficulties in producing.
Summary of the invention
The object of the application is the weld jig providing a kind of aircraft unimach flap-track structural member electron beam welding.
A kind of weld jig of aircraft flap rail structure part electron-bombardment welding, this structural member comprise one have the sliding track body in multiple abdominal cavity and polylith corresponding with abdominal cavity needs welding web, its feature is a flat rigid structure at the body of this fixture, body is provided with multiple be located by connecting hole corresponding with sliding track body profile, locating piece and multiple fenestra corresponding with sliding track body abdominal cavity, the border of this fenestra is greater than the border in corresponding sliding track body abdominal cavity, the connector of a shaft-like is respectively provided with in the middle part of the two ends of body, two legs are separately had to be positioned at the two ends of body, the top of leg is auricle groove, fix with latch in the auricle groove that this connector is supported on leg top, two ends respectively.
During use, sliding track body securing member is fixed on a side surface of chuck body by locating hole, locating piece, the abdominal cavity of sliding track body is corresponding on the fenestra of chuck body; Electron-bombardment welding is adopted the web of correspondence to be welded on a side surface in sliding track body abdominal cavity according to the order of adjacent spaces; Again by fixing for chuck body 180 degree upset, make sliding track body downward, still adopt electron-bombardment welding according to the order of adjacent spaces by the fenestra in chuck body, the web of correspondence is welded on the opposite side surface in sliding track body abdominal cavity.
The invention has the advantages that: it is fixing that workpiece can be carried out 180 degree of upsets by the weld jig that 1) the present invention proposes, and realizes workpiece clamped one time, the operation of two sides welding, reduces clamping times, improves welding quality, effectively prevents the welding deformation of workpiece.
Below in conjunction with embodiment accompanying drawing, the application is described in further detail.
Accompanying drawing explanation
Fig. 1 is the signal of aircraft flap rail structure part body
Fig. 2 is the weld jig structural representation that the application proposes
Fig. 3 is the signal of aircraft flap rail structure part welding method
Fig. 4 is the rollover states signal of Fig. 3
Number description: 1 sliding track body, 2 abdominal cavities, 2-1 first abdominal cavity, 2-2 second abdominal cavity, 2-3 the 3rd abdominal cavity, 2-4 the 4th abdominal cavity, 2-5 the 5th abdominal cavity, 2-6 the 6th abdominal cavity, 3 chuck body, 4 are located by connecting hole, 5 keepers, 6 fenestras, 7 bearings, 8 latches, 9 connectors, 10 compressing members, 11 securing members, 12 briquettings, 13 webs, 14 weld seams
Detailed description of the invention
See accompanying drawing, embodiment shows a kind of welding method and weld jig of aircraft flap rail structure part.Aircraft slide rail is primarily of compositions such as cross section " work " font slideway, solid and middle hollow slab, connecting axle and reinforcements, and its material is unmanageable unimach.The sliding track body 1 of flap-track as shown in Figure 1, it there are six adjacent abdominal cavities 2, first abdominal cavity 2-1, the second abdominal cavity 2-2, the 3rd abdominal cavity 2-3, the 4th abdominal cavity 2-4, the 5th abdominal cavity 2-5 and the 6th abdominal cavity 2-6, technological requirement needs the thin web 13 of welding and abdominal cavity form fit in the both sides in each abdominal cavity.
In order to the distortion in controlling to weld with improve working (machining) efficiency, a kind of aircraft flap slide rail weld jig of the application's specialized designs, as shown in Figure 2.This chuck body 3 is flat rigid structures, chuck body 3 is provided with multiple be located by connecting hole 4 corresponding with sliding track body profile, locating piece 5 and multiple fenestra 6 corresponding with sliding track body abdominal cavity, the border of this fenestra 6 is greater than the border in sliding track body abdominal cavity 2 at least about 15mm, so that implement welding at the reverse side of chuck body.The connector 9 of a shaft-like is respectively provided with in the middle part of the two ends of body 3, two legs 7 are separately had to be positioned at the two ends of body, the top of leg 7 is auricle grooves, auricle is provided with connecting hole, the shaft-like connector 9 at chuck body two ends is supported in the top auricle groove of two ends leg 7 respectively, separately has latch 8 chuck body and leg to be fixed by the connecting hole on connector 9 and auricle.
Before welding, sliding track body 1 securing member 11 and compressing member 10 are fixed on a side surface of chuck body by locating hole 4, locating piece 5, make abdominal cavity 2 correspondence of sliding track body on the fenestra 6 of chuck body; 3) electron-bombardment welding is adopted the web 13 of correspondence to be welded on a side surface in sliding track body abdominal cavity 2 according to the order of adjacent spaces; Namely welding sequence is, first welds the web of the first 2-1 side, abdominal cavity, then welds the web of the 3rd 2-3 side, abdominal cavity, then welds the web of the 5th 2-5 side, abdominal cavity.Then, by fixing for chuck body 180 degree upset, make sliding track body 1 downward, still electron-bombardment welding is adopted according to the order of adjacent spaces by the fenestra 6 in chuck body 3, the web of correspondence is welded on the opposite side surface in sliding track body abdominal cavity, namely first weld the web of the first abdominal cavity 2-1 opposite side, then weld the web of the 3rd abdominal cavity 2-3 opposite side, then weld the web of the 5th abdominal cavity 2-5 opposite side; 4) again by fixing for chuck body 180 degree upset, make sliding track body upwards, according to step 3) principle, after according to the order of adjacent spaces the web of correspondence being welded on a side surface in remaining sliding track body abdominal cavity, namely the web of the second 2-2 side, abdominal cavity is welded, weld the web of the 4th 2-4 side, abdominal cavity again, then weld the web of the 6th 2-6 side, abdominal cavity.Turnover fixture body 180 degree is fixed again, finally the web of correspondence is welded on the opposite side surface in remaining sliding track body abdominal cavity, namely weld the web of the second abdominal cavity 2-2 opposite side, then weld the web of the 4th abdominal cavity 2-4 opposite side, then weld the web of the 6th abdominal cavity 2-6 opposite side.
Each block web 13 that both sides, abdominal cavity 2 are welded is all a closed weld seam 14, for the weld seam closed, welding process is unavoidable causes web to become arch or one jiao of tilting because of being heated uneven, and between electron beam welding characteristic, middle web also cannot be fixed by chuck body, only have and solve web intermediate projections or warpage by the mode of load-carrying in the middle of web, in enforcement, first web 13 is seated in a side surface in corresponding abdominal cavity 2, the briquetting 12 suppressing a heavily about 15-20 kilogram weight again at the upper surface of web again carries out web location, multiple spot linear interpolation is adopted at the straightway of weld seam during welding, multiple spot circular interpolation is adopted at the arc section of weld seam, a distance is controlled the requirement that can meet electron beam welding within the specific limits.
Claims (1)
1. the weld jig of an aircraft flap rail structure part electron-bombardment welding, this structural member comprise one have the sliding track body in multiple abdominal cavity and polylith corresponding with abdominal cavity needs welding web, its feature is a flat rigid structure at the body of this fixture, body is provided with multiple be located by connecting hole corresponding with sliding track body profile, locating piece and multiple fenestra corresponding with sliding track body abdominal cavity, the border of this fenestra is greater than the border in corresponding sliding track body abdominal cavity, the connector of a shaft-like is respectively provided with in the middle part of the two ends of body, two legs are separately had to be positioned at the two ends of body, the top of leg is auricle groove, fix with latch in the auricle groove that this connector is supported on leg top, two ends respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520373004.4U CN204725061U (en) | 2015-06-02 | 2015-06-02 | A kind of weld jig of aircraft flap rail structure part electron-bombardment welding |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520373004.4U CN204725061U (en) | 2015-06-02 | 2015-06-02 | A kind of weld jig of aircraft flap rail structure part electron-bombardment welding |
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| CN204725061U true CN204725061U (en) | 2015-10-28 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201520373004.4U Expired - Fee Related CN204725061U (en) | 2015-06-02 | 2015-06-02 | A kind of weld jig of aircraft flap rail structure part electron-bombardment welding |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104999208A (en) * | 2015-06-02 | 2015-10-28 | 中航飞机股份有限公司西安飞机分公司 | Welding jig for conducting vacuum electron beam welding on airplane flap sliding rail structural part |
| GB2537717A (en) * | 2015-02-23 | 2016-10-26 | Boeing Co | Method, system and apparatus for assembling a composite wing skin with stiffeners |
-
2015
- 2015-06-02 CN CN201520373004.4U patent/CN204725061U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2537717A (en) * | 2015-02-23 | 2016-10-26 | Boeing Co | Method, system and apparatus for assembling a composite wing skin with stiffeners |
| GB2537717B (en) * | 2015-02-23 | 2017-05-17 | Boeing Co | Composite wing skin assembly jig |
| US9914549B2 (en) | 2015-02-23 | 2018-03-13 | The Boeing Company | Method, system and apparatus for assembling a composite wing skin with stiffeners |
| CN104999208A (en) * | 2015-06-02 | 2015-10-28 | 中航飞机股份有限公司西安飞机分公司 | Welding jig for conducting vacuum electron beam welding on airplane flap sliding rail structural part |
| CN104999208B (en) * | 2015-06-02 | 2016-08-24 | 中航飞机股份有限公司西安飞机分公司 | A kind of vacuum electron beam welding method of aircraft flap rail structure part |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20151028 Termination date: 20170602 |