CN204894565U - Machine carries whole shaping structure of external combined material covering - Google Patents
Machine carries whole shaping structure of external combined material covering Download PDFInfo
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- CN204894565U CN204894565U CN201520673451.1U CN201520673451U CN204894565U CN 204894565 U CN204894565 U CN 204894565U CN 201520673451 U CN201520673451 U CN 201520673451U CN 204894565 U CN204894565 U CN 204894565U
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Abstract
The utility model belongs to the technical field of the machine carries external technique and specifically relates to a machine carries whole shaping structure of external combined material covering. A machine carries whole shaping structure of external combined material covering, includes the combination frock of compriseing mould and metal crate, metal crate sets up in the tip of mould, and metal crate's upper and lower both ends have been fastened first inserting respectively and are inserted with the second, the mould is the columnar structure that a plurality of mold core block assemblings become, the combination frock is spread in proper order outward and is posted the preimpregnation bed of material and vacuum auxiliary material layer. The utility model discloses to constitute the combination frock with metal crate by the mould, and then realize that covering and metal crate solidify altogether, and be convenient for install and make things convenient for the drawing of patterns, adopt the utility model discloses the combined material skin structure of preparation has following advantage: 1. It carries external weight to alleviate the machine, 2. Reduce the use and the assemble duration of standard component, 3. Reduce part manufacturing cost by a wide margin, 4. The shaping is covered to whole the shop, and mechanical properties is good, 5. Subsequent cutting and assembly process are simple.
Description
Technical field
The utility model relates to airborne plug-in technical field, especially a kind of airborne plug-in composite material skin integral forming structure.
Background technology
Airborne plug-in be the conventional airborne equipment of helicopter, transporter and unmanned plane, it generally adopts aluminum alloy outer cover machining shaping, then is assembled by mechanical connection manners such as rivet, be spirally connected.As shown in Figure 1, existing composite material skin structure, its inside is typical metal framework, and outside is composite material skin.
General composite material skin first adopts sectional forming, then the end frame of every section and metal framework assembles.This process is shaping relatively simple, but subsequent treatment is more loaded down with trivial details.Mould generally adopts female mould structure, and by prepreg and honeycomb core paving successively, after shaping end, composite material skin uses cutting machine or Digit Control Machine Tool processing according to metal frame segment length, and then is assembled in metal frame section, carries out riveting, be spirally connected work.If have a kind of structure can by covering and metal framework one-body molded, will much follow-up operation be decreased.
Utility model content
The technical problems to be solved in the utility model is: based on the problems referred to above, provides a kind of airborne plug-in composite material skin integral forming structure.
The utility model solves the technical scheme that its technical problem adopts: a kind of airborne plug-in composite material skin integral forming structure, comprise the assembled tool be made up of mould and metal framework, described metal framework is arranged at the end of mould, the upper/lower terminal of metal framework is fastened with the first insert and the second insert respectively, described mould is the column structure that multiple core pieces is assembled into, and described assembled tool is affixed with prepreg and vacuum auxiliary material layer outward successively.
Further, described core pieces comprises the first core pieces, the second core pieces, the 3rd core pieces, the 4th core pieces and the 5th core pieces, described first core pieces is positioned at mold center, and be rectangular structure, be symmetrical arranged the 3rd core pieces and the second core pieces in the first core pieces left and right sides, the 4th core pieces and the 5th core pieces are set in the bilateral symmetry up and down of the first core pieces.
The beneficial effects of the utility model are: the utility model will form assembled tool by mould and metal framework, and then realize covering and metal framework co-curing, be convenient to install and conveniently stripped, adopt the utility model making composite material skin structure tool have the following advantages:
1. alleviate airborne plug-in weight;
2. reduce use and the installation time of standard component;
3. significantly reduce part manufacturing cost;
4. overall paving is covered shaping, good mechanical performance;
5. follow-up cutting and assembly technology simple.
Accompanying drawing explanation
Below in conjunction with drawings and Examples, the utility model is further illustrated.
Fig. 1 is existing composite material skin structure.
Fig. 2 is structural representation of the present utility model.
Fig. 3 is the structural representation after the utility model solidification.
In figure: 1. mould, 2. metal framework, 3. the first insert, 4. the second insert, 5. the first core pieces, 6. the second core pieces, 7. the 3rd core pieces, 8. the 4th core pieces, 9. the 5th core pieces, 10. composite material skin.
Detailed description of the invention
By reference to the accompanying drawings the utility model is described in further detail now.These accompanying drawings are the schematic diagram of simplification, only basic structure of the present utility model are described in a schematic way, and therefore it only shows the formation relevant with the utility model.
As shown in figures 2-3, a kind of airborne plug-in composite material skin integral forming structure, comprise the assembled tool be made up of mould 1 and metal framework 2, metal framework 2 is arranged at the end of mould 1, the upper/lower terminal of metal framework 2 is fastened with the first insert 3 and the second insert 4 respectively, mould 1 is the column structure that multiple core pieces is assembled into, and assembled tool is affixed with prepreg and vacuum auxiliary material layer outward successively.
In the present embodiment, core pieces comprises the first core pieces 5, second core pieces 6, the 3rd core pieces 7, the 4th core pieces 8 and the 5th core pieces 9, first core pieces 5 is positioned at mould 1 center, and be rectangular structure, be symmetrical arranged the 3rd core pieces 7 and the second core pieces 6 in first core pieces 5 left and right sides, the 4th core pieces 8 and the 5th core pieces 9 are set in the bilateral symmetry up and down of the first core pieces 5.
Time shaping, as shown in Figure 2, install the first core pieces 5, second core pieces 6, the 3rd core pieces 7, the 4th core pieces 8 and the 5th core pieces 9 successively, and fastening; Then the first insert 3 and the second insert 4 are anchored on the upper and lower end of metal framework 2; Confirm that the docking of assembled tool surface flushes, after transitions smooth, paving prepreg and vacuum auxiliary material layer successively thereon; Finally, solidification of hot-press tank is put into after connecting vacuum line and thermocouple; Frock integrally curing to be combined is complete, removes vacuum auxiliary material layer, first the first core pieces 5 is extracted out, then dismantle the 4th core pieces 8, the 3rd core pieces 7, second core pieces 6 and the 5th core pieces 9 successively from top to bottom.Thus, as shown in Figure 3, whole integrated composite material skin structure has manufactured, and after to be cut, then the first insert 3 and the second insert 4 is taken out.
With above-mentioned according to desirable embodiment of the present utility model for enlightenment, by above-mentioned description, relevant staff in the scope not departing from this utility model technological thought, can carry out various change and amendment completely.The technical scope of this utility model is not limited to the content on description, must determine its technical scope according to right.
Claims (2)
1. an airborne plug-in composite material skin integral forming structure, it is characterized in that: comprise the assembled tool be made up of mould (1) and metal framework (2), described metal framework (2) is arranged at the end of mould (1), the upper/lower terminal of metal framework (2) is fastened with the first insert (3) and the second insert (4) respectively, the column structure that described mould (1) is assembled into for multiple core pieces, described assembled tool is affixed with prepreg and vacuum auxiliary material layer outward successively.
2. the airborne plug-in composite material skin integral forming structure of one according to claim 1, it is characterized in that: described core pieces comprises the first core pieces (5), second core pieces (6), 3rd core pieces (7), 4th core pieces (8) and the 5th core pieces (9), described first core pieces (5) is positioned at mould (1) center, and be rectangular structure, the 3rd core pieces (7) and the second core pieces (6) is symmetrical arranged in the first core pieces (5) left and right sides, in the bilateral symmetry up and down of the first core pieces (5), the 4th core pieces (8) and the 5th core pieces (9) are set.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520673451.1U CN204894565U (en) | 2015-09-02 | 2015-09-02 | Machine carries whole shaping structure of external combined material covering |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520673451.1U CN204894565U (en) | 2015-09-02 | 2015-09-02 | Machine carries whole shaping structure of external combined material covering |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204894565U true CN204894565U (en) | 2015-12-23 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201520673451.1U Active CN204894565U (en) | 2015-09-02 | 2015-09-02 | Machine carries whole shaping structure of external combined material covering |
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| CN (1) | CN204894565U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108568976A (en) * | 2018-05-16 | 2018-09-25 | 湖北三江航天万峰科技发展有限公司 | Lighting abnormity section structure and nacelle production method |
| CN109353025A (en) * | 2018-09-17 | 2019-02-19 | 江西洪都航空工业集团有限责任公司 | A kind of thermoplastic short fiber answers material cabin moulding process and structure |
-
2015
- 2015-09-02 CN CN201520673451.1U patent/CN204894565U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108568976A (en) * | 2018-05-16 | 2018-09-25 | 湖北三江航天万峰科技发展有限公司 | Lighting abnormity section structure and nacelle production method |
| CN109353025A (en) * | 2018-09-17 | 2019-02-19 | 江西洪都航空工业集团有限责任公司 | A kind of thermoplastic short fiber answers material cabin moulding process and structure |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |