CN203062651U - Assembly fixture for outer wing leading edge skeleton - Google Patents
Assembly fixture for outer wing leading edge skeleton Download PDFInfo
- Publication number
- CN203062651U CN203062651U CN 201320046153 CN201320046153U CN203062651U CN 203062651 U CN203062651 U CN 203062651U CN 201320046153 CN201320046153 CN 201320046153 CN 201320046153 U CN201320046153 U CN 201320046153U CN 203062651 U CN203062651 U CN 203062651U
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- CN
- China
- Prior art keywords
- skeleton
- framework
- leading edge
- supporting plates
- outer nose
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- 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 - Lifetime
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Abstract
The utility model discloses an assembly fixture for an outer wing leading edge skeleton, which comprises a framework and a plurality of supporting plates used for clamping the skeleton, wherein the framework comprises an assembly table board horizontally and upwardly arranged, the supporting plates are arranged on the assembly table board, clamping grooves for placing the skeleton and hook-shaped bolt compactors for positioning and clamping the skeletons are arranged on the supporting plates; support legs are arranged below the framework; and the supporting plates are connected and fixed on the assembly table board through an angle seat. The assembly fixture is simple in structure, suitable for assembling the outer wing leading edge skeleton of an airplane, and favorable for improving the assembly efficiency of the outer wing leading edge skeleton.
Description
Technical field
The utility model relates to the technical field of airplane structural parts assembly tooling, relates in particular to a kind of outer nose of wing skeleton assembly jig.
Background technology
Along with continuous advancement in technology, the physical dimension of aircraft is also increasing, fitted position for the outer nose of wing skeleton of aircraft is also increasing, requirements such as the accuracy of manufacture are also improving constantly, and need carry out assembling work repeatedly, for making things convenient for the workman to carry out assembling work, and reduce the distortion of structure in the assembling process and guarantee accurately the location and clamp the purpose that realizes reducing labor strength and improve workman's efficiency of assembling.Those skilled in the art be devoted to develop always a kind of simple in structure, be applicable to the outer nose of wing skeleton assembling of aircraft, be conducive to improve the outer nose of wing skeleton assembly jig of outer nose of wing skeleton efficiency of assembling.
The utility model content
Because above-mentioned the deficiencies in the prior art, the utility model proposes a kind of simple in structure, be applicable to the outer nose of wing skeleton assembling of aircraft, be conducive to improve the outer nose of wing skeleton assembly jig of outer nose of wing skeleton efficiency of assembling.
For achieving the above object, the utility model provides a kind of outer nose of wing skeleton assembly jig, comprising: framework and some supporting plates for the clamping skeleton; Described framework comprises the assembling table top that a level is arranged up, and some described supporting plates are arranged on the described assembling table top, offers on the described supporting plate for the draw-in groove of placing described skeleton with for locating the hook bolt compactor that clamps described skeleton.
Preferable, the below of described framework is provided with feet.
Preferable, described supporting plate is fastened on the described assembling table top by the angle seat.
The beneficial effect of a kind of outer nose of wing skeleton assembly jig of the utility model is as follows:
Outer nose of wing skeleton assembly jig of the present utility model is simple in structure, is applicable to the outer nose of wing skeleton assembling of aircraft, is conducive to improve the efficiency of assembling of outer nose of wing skeleton.The utility model can be according to the assembling mesa dimensions of outer nose of wing skeleton appearance and size tectonic framework, adaptive arranges supporting plate at described assembling table top, can realize outer nose of wing skeletal fixation clamping on described supporting plate, can very easily outer nose of wing skeleton be positioned in conjunction with supporting plate groove and hook bolt compactor, can realize that the workman joins at the enterprising luggage of assembling table top, be very suitable for the assembling work of outer nose of wing skeleton, effectively reduce working strength of workers, improved operating efficiency.
Be described further below with reference to the technique effect of accompanying drawing to design of the present utility model, concrete structure and generation, to understand the purpose of this utility model, feature and effect fully.
Description of drawings
Fig. 1 is the outer nose of wing skeleton assembly jig structural representation of present embodiment.
Fig. 2 is the local enlarged diagram at the A place of Fig. 1.
The specific embodiment
As depicted in figs. 1 and 2, a kind of outer nose of wing skeleton assembly jig of present embodiment comprises: framework 1 and some supporting plates 2 for the clamping skeleton; Framework 1 comprises the assembling table top 3 that a level is arranged up, and some supporting plates 2 are arranged on the assembling table top 3, offers on the supporting plate 2 for the draw-in groove 6 of placing skeleton with for locating the hook bolt compactor 5 that clamps described skeleton.
Concrete, the below of the framework 1 of present embodiment is provided with feet 4, can further facilitate the height of adjusting the assembling table top, and horizontal base makes it be fit to the workman more and uses.Exemplary, the supporting plate 2 of present embodiment is fastened on the assembling table top 3 by angle seat 7, and is simple and reliable for structure.
Exemplary, the concrete application of a kind of outer nose of wing skeleton assembly jig of present embodiment is as follows:
Present embodiment is according to outer nose of wing frame design requirement to be processed, the assembling table top of tectonic framework 1, and simultaneously adaptive arranges supporting plate 2 at the assembling table top.The workman on supporting plate 2, uses hook bolt compactor 5 to compress the skeletal fixation clamping.Wherein, the supporting plate 2 that present embodiment adopts and be arranged on draw-in groove 6 on the supporting plate 2 and the quantity of hook bolt the compactor 5 and position is set can adjusts according to actual needs can also arrange other skeleton positioner as required.Skeleton is after clamping finishes on the assembling table top, and the workman assembly manipulation such as rivets to skeleton on the nose of wing skeleton assembly jig outside.
More than describe preferred embodiment of the present utility model in detail.Should be appreciated that those of ordinary skill in the art need not creative work and just can make many modifications and variations according to design of the present utility model.Therefore, all technical staff in the art comply with design of the present utility model on the basis of existing technology by the available technical scheme of logical analysis, reasoning, or a limited experiment, all should be in the determined protection domain by claims.
Claims (3)
1. an outer nose of wing skeleton assembly jig is characterized in that comprising: framework and some supporting plates for the clamping skeleton; Described framework comprises the assembling table top that a level is arranged up, and some described supporting plates are arranged on the described assembling table top, offers on the described supporting plate for the draw-in groove of placing described skeleton with for locating the hook bolt compactor that clamps described skeleton.
2. outer nose of wing skeleton assembly jig as claimed in claim 1, it is characterized in that: the below of described framework is provided with feet.
3. outer nose of wing skeleton assembly jig as claimed in claim 1, it is characterized in that: described supporting plate is fastened on the described assembling table top by the angle seat.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320046153 CN203062651U (en) | 2013-01-28 | 2013-01-28 | Assembly fixture for outer wing leading edge skeleton |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320046153 CN203062651U (en) | 2013-01-28 | 2013-01-28 | Assembly fixture for outer wing leading edge skeleton |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203062651U true CN203062651U (en) | 2013-07-17 |
Family
ID=48761477
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201320046153 Expired - Lifetime CN203062651U (en) | 2013-01-28 | 2013-01-28 | Assembly fixture for outer wing leading edge skeleton |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203062651U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105905311A (en) * | 2015-02-23 | 2016-08-31 | 波音公司 | Method, System and Apparatus for Assembling a Composite Wing Skin with Stiffeners |
| CN106002784A (en) * | 2016-07-28 | 2016-10-12 | 苏州高通机械科技有限公司 | Positioning and diameter varying supporting fixture |
| CN109877746A (en) * | 2019-04-03 | 2019-06-14 | 西安飞机工业（集团）有限责任公司 | A kind of intensive style leading edge tooling and its assembly method |
-
2013
- 2013-01-28 CN CN 201320046153 patent/CN203062651U/en not_active Expired - Lifetime
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105905311A (en) * | 2015-02-23 | 2016-08-31 | 波音公司 | Method, System and Apparatus for Assembling a Composite Wing Skin with Stiffeners |
| 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 |
| CN105905311B (en) * | 2015-02-23 | 2020-07-14 | 波音公司 | Method, system and apparatus for assembling composite wing skins with stiffeners |
| CN106002784A (en) * | 2016-07-28 | 2016-10-12 | 苏州高通机械科技有限公司 | Positioning and diameter varying supporting fixture |
| CN109877746A (en) * | 2019-04-03 | 2019-06-14 | 西安飞机工业（集团）有限责任公司 | A kind of intensive style leading edge tooling and its assembly method |
| CN109877746B (en) * | 2019-04-03 | 2023-06-23 | 西安飞机工业（集团）有限责任公司 | Intensive front edge tool and assembly method thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130717 |