CN101342942A - Disposal solidifying and forming technique for frame and outer panel skin of wing profile - Google Patents
Disposal solidifying and forming technique for frame and outer panel skin of wing profile Download PDFInfo
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- CN101342942A CN101342942A CNA2008101369770A CN200810136977A CN101342942A CN 101342942 A CN101342942 A CN 101342942A CN A2008101369770 A CNA2008101369770 A CN A2008101369770A CN 200810136977 A CN200810136977 A CN 200810136977A CN 101342942 A CN101342942 A CN 101342942A
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Abstract
The invention provides a technique for curing and molding an airfoil frame and an aircraft skin at one time. The technique adopts built-in detachable grouped dies; the dies are transversely divided into different die groups by carlings, and each die group is composed of a set of module and a central slideway; the module and the central slideway in each group can slide relatively and can be taken out from the die cavity sequentially; all the bulkheads and the carlings are provided with concave grooves which match with the airfoil frame in shape; the ventral shields of the airfoil carlings are the combination of composite material and I-shaped alloy plates; bulkhead fibre is laid inside the concave grooves through winding. After the frame fiber is laid, the skin fibre is uniformly laid, forming a hatch rim frame the same as the bulkheads; after that, a vacuum bag is arranged at the outer surface and grease injection and vacuum die press molding are adopted; the frame and the aircraft skin are molded and cured at one time through the technique of electron beam heating, high temperature stove heating or curing at normal temperature according the compounding technological requirements of the fibre resin substrate. The invention has fewer accessories, lighter weight, short production period, low cost and high safety factor and the anti-corrosion capability and anti-fatigue capability are improved by more than two times.
Description
(1) technical field
The present invention relates to the aircraft manufacturing technology, be specifically related to a kind of aerofoil profile framework and covering solidified forming technology.
(2) background technology
Tradition aerofoil profile framework and covering forming technology are to assemble the aerofoil profile metal framework earlier, and beam, floor, long purlin are arranged in the framework; Rivet afterwards or the splicing covering, required number of parts is more again, complex process, and efficient is low; Simultaneously weight is big, and anti-corrosion capability, fatigue resistance are low, the operation cost height.
(3) summary of the invention
The object of the present invention is to provide a kind of part few, weight is few, and is with short production cycle, and cost is low, and resistance to corrosion, anti-fatigue ability improve more than 2 times, aerofoil profile framework that safety factor is high and covering disposal solidifying forming process.
The object of the present invention is achieved like this: adopt built-in detachable grouping mould, mould is cut apart by longeron in the horizontal and is formed different set of molds, be made up of a pack module and center slide rail for every group, module and its center slide rail in every group can slide and take out from die cavity successively after shaping mutually; Be provided with the groove consistent at all bulkheads, longeron place with outling of truss; Aerofoil profile longeron web is the fabricate block of composite material and " I " shape alloy sheets; The bulkhead fiber adopts the winding method to lay in groove: web fiber miter angle is laid; Lay at wing plate fiber 0 degree angle; Covering fiber miter angle is laid; After finishing the framework fleece-laying, unified covering fiber, the same flap edge frame that forms laid with bulkhead; Put vacuum bag at outside face afterwards, adopt the greasing of vacuum diaphragm platen press to be shaped, utilize the electron ray heating or heating or normal temperature cure technology implementation framework and the shaping of covering disposal solidifying in high temperature furnace according to fiber resin matrix bluk recombination technological requirement.
The present invention also has some technical characterictics like this:
1, the detachable built-in composite die of described employing, front-axle beam is a pack module to leading edge, the back rest is a pack module to trailing edge, for many girder constructions, it between the Liang Yuliang pack module, the front and back module is made up of 6 moulds and a center slide rail respectively, and middle module is made up of 8 moulds and a center slide rail, utilizes preceding mould and the back group mould organized of the fixing assembling of the logical bolt of fixed mould piece;
2, described fleece-laying order is as follows: (1) separately respectively organizes earlier mould, is laterally adopting the winding method to lay bulkhead groove fiber in the bulkhead groove, and the fleece-laying direction is consistent with groove direction; (2) laid and lay longeron web fiber behind the bulkhead groove fiber, the fleece-laying direction vertically becomes miter angle with longeron; (3) utilize anchor clamps to close up the front and back set of molds, lay longeron wing plate fiber, the fleece-laying direction vertically becomes 0 degree angle with longeron; (4) lay the covering fiber, the fleece-laying direction vertically becomes miter angle with longeron; (5) vacuum is inhaled in external vacuum diaphragm greasing; (6) utilize inspect by instrument deep-seated blowhole defective; (7) defective is got rid of in vibrations; (8) be heating and curing;
3, after the described curing, pull down fixing logical bolt and anchor clamps, the center slide rail 13 of the center slide rail 8 of group mould, back group mould before taking out earlier, then, employing is taken out successively to the moving method of center string and is respectively organized the mould piece, repairs logical bolt process hole and surface deficiency at last, finishes whole wing;
5, in described fibre resin based composites and " I " font alloy sheets fabricate block, fiber can be carbon fiber, boron fiber, E-glass fibre, aramid fiber, resin is a liquid-state epoxy resin, and beam is that " I " font alloy sheets and composite material fabricate block are web " worker " font structure.
Forming technology of the present invention is at aircraft wing and huge wind blade forming technology.Technology of the present invention and traditional handicraft are essentially different.The tradition forming technology is to assemble the aerofoil profile metal framework earlier, and beam, floor, long purlin are arranged in the framework; Rivet afterwards or the splicing covering, required number of parts is more again, complex process, and efficient is low; Simultaneously weight is big, and anti-corrosion capability, fatigue resistance are low, the operation cost height.Aerofoil profile of the present invention is formed with following characteristics.1, be to adopt fibre resin based composites and " I " font alloy sheets fabricate block, fiber can be carbon fiber, boron fiber, E-glass fibre, aramid fiber, and resin is a liquid-state epoxy resin; 2, but it adopts built-in packet disassembly composite die on manufacturing process; 3, because aerofoil profile in lumen, take out inner module after being shaped, therefore cancelled horizontal ribbed, generation be T shape framework with the covering solidified forming, we are referred to as T shape bulkhead; 4, beam is that " I " font alloy sheets and composite material fabricate block are web " worker " font structure, makes aerofoil profile have higher rigidity and intensity; 5,, be provided with the required groove of said frame shaping in all bulkheads, longeron position from the composite die outside; 6, last external vacuum diaphragm adopts the greasing of vacuum diaphragm platen press to be shaped.
Compare with traditional handicraft by the aircraft wing that adopts above-mentioned technology manufacturing, number of parts has reduced 99%, only form by the several parts that comprise flap, weight reduces 50%, production cycle shortens above 80%, and cost reduces by 30%, and resistance to corrosion, anti-fatigue ability improve more than 2 times, thereby improved safety factor, reduced operation cost.
(4) description of drawings
Fig. 1 is the mould scheme drawing of the specific embodiment;
Fig. 2 will soon combine scheme drawing with longeron " I " font alloy sheets 18 after bulkhead groove fiber 16,20 and longeron web fiber 17,19 have been laid;
Fig. 3 is that the front and back set of molds is combined by anchor clamps 22, lays wing plate fiber 23 and covering fiber 21 scheme drawings;
After Fig. 4 is solidified forming, pull down logical bolt and center slide rail scheme drawing;
Fig. 5 is the aerofoil profile scheme drawing of pulling down behind whole moulds;
Fig. 6 is the horizontal section scheme drawing of aerofoil profile when solidifying.
(5) specific embodiment
The present invention is further illustrated below in conjunction with accompanying drawing:
Fig. 1-Fig. 6 is the single-beam airfoil structure, and the multi-spar wing type structure principle that is shaped with it is identical.In conjunction with Fig. 1, the present embodiment mould comprises detachable built-in composite die, front-axle beam is a pack module to leading edge, the back rest is a pack module to trailing edge, for many girder constructions, it between the Liang Yuliang pack module, the front and back module is made up of 6 moulds and a center slide rail respectively, preceding group mould comprises horizontal bulkhead groove 1, " worker " tee beam wing plate groove 2, the leading edge shaping die 6 of preceding group mould, the shaping die up and down 7 of preceding group mould, the center slide rail 8 of preceding group mould, the longeron web shaping die 10 of shaping die 9 and preceding group of mould about the longeron of preceding group mould, back group mould comprises " worker " tee beam wing plate groove 3, horizontal bulkhead groove 4, the longeron of back group mould is shaping die 11 up and down, the longeron web shaping die 12 of back group mould, the center slide rail 13 of back group mould, the trailing edge shaping die 15 of the shaping die up and down 14 of back group mould and back group mould, middle module is made up of 8 moulds and a center slide rail.Organize mould and back group mould before utilizing the logical bolt 5 fixing assemblings of fixed mould piece.
In conjunction with Fig. 2, what Fig. 2 showed is soon to combine with longeron " I " font alloy sheets 18 after bulkhead groove fiber 16,20 and longeron web fiber 17,19 have been laid.What Fig. 3 showed is that the front and back set of molds is combined by anchor clamps 22, lays wing plate fiber 23 and covering fiber 21.
The fleece-laying order is as follows: (1) separately respectively organizes earlier mould, is laterally adopting the winding method to lay bulkhead groove fiber 16,20 in the bulkhead groove, and the fleece-laying direction is consistent with groove direction; (2) laid bulkhead groove fiber 16,20 backs and laid longeron web fiber 17,19, the fleece-laying direction vertically becomes miter angle (in conjunction with Fig. 2) with longeron; (3) utilize anchor clamps 22 closure front and back set of molds, lay longeron wing plate fiber 23, the fleece-laying direction vertically becomes 0 degree angle with longeron; (4) lay covering fiber 21, the fleece-laying direction vertically becomes miter angle (in conjunction with Fig. 3) with longeron; (5) vacuum is inhaled in external vacuum diaphragm greasing; (6) utilize inspect by instrument deep-seated blowhole defective; (7) defective is got rid of in vibrations; (8) be heating and curing.
Behind the complete curing, pull down fixing logical bolt and anchor clamps, take out center slide rail 8, the back of preceding group mould according to mould structure characteristics elder generation and organize the center slide rail 13 of mould (in conjunction with Fig. 4, Fig. 4 shows be solidified forming after, pull down logical bolt and center slide rail), then, adopt to take out successively and respectively organize mould piece (in conjunction with Fig. 4, Fig. 5, Fig. 5 shows is the aerofoil profile of pulling down behind whole moulds) to the moving method of center string.
Repair logical bolt process hole and surface deficiency at last, finish whole wing.
Claims (5)
1, a kind of aerofoil profile framework and covering disposal solidifying forming process, it is characterized in that adopting built-in detachable grouping mould, mould is cut apart by longeron in the horizontal and is formed different set of molds, be made up of a pack module and center slide rail for every group, module and its center slide rail in every group can slide and take out from die cavity successively after shaping mutually; Be provided with the groove consistent at all bulkheads, longeron place with outling of truss; Aerofoil profile longeron web is the fabricate block of composite material and " I " shape alloy sheets; The bulkhead fiber adopts the winding method to lay in groove: web fiber miter angle is laid; Lay at wing plate fiber 0 degree angle; Covering fiber miter angle is laid; After finishing the framework fleece-laying, unified covering fiber, the same flap edge frame that forms laid with bulkhead; Put vacuum bag at outside face afterwards, adopt the greasing of vacuum diaphragm platen press to be shaped, utilize the electron ray heating or heating or normal temperature cure technology implementation framework and the shaping of covering disposal solidifying in high temperature furnace according to fiber resin matrix bluk recombination technological requirement.
2, aerofoil profile framework according to claim 1 and covering disposal solidifying forming process, it is characterized in that the detachable built-in composite die of described employing, front-axle beam is a pack module to leading edge, the back rest is a pack module to trailing edge, for many girder constructions, between the Liang Yuliang pack module, the front and back module is made up of 6 moulds and a center slide rail respectively, middle module is made up of 8 moulds and a center slide rail, utilizes fixing assembling preceding group mould of the logical bolt of fixed mould piece and back group mould.
3, aerofoil profile framework according to claim 2 and covering disposal solidifying forming process, it is characterized in that described fleece-laying order is as follows: (1) separately respectively organizes earlier mould, laterally adopting the winding method to lay bulkhead groove fiber in the bulkhead groove, the fleece-laying direction is consistent with groove direction; (2) laid and lay longeron web fiber behind the bulkhead groove fiber, the fleece-laying direction vertically becomes miter angle with longeron; (3) utilize anchor clamps to close up the front and back set of molds, lay longeron wing plate fiber, the fleece-laying direction vertically becomes 0 degree angle with longeron; (4) lay the covering fiber, the fleece-laying direction vertically becomes miter angle with longeron; (5) vacuum is inhaled in external vacuum diaphragm greasing; (6) utilize inspect by instrument deep-seated blowhole defective; (7) defective is got rid of in vibrations; (8) be heating and curing.
4, aerofoil profile framework according to claim 3 and covering disposal solidifying forming process, after it is characterized in that described curing, pull down fixing logical bolt and anchor clamps, the center slide rail 13 of the center slide rail 8 of group mould, back group mould before taking out earlier, then, employing is taken out successively to the moving method of center string and is respectively organized the mould piece, repairs logical bolt process hole and surface deficiency at last, finishes whole wing.
5, aerofoil profile framework according to claim 4 and covering disposal solidifying forming process, it is characterized in that in described fibre resin based composites and " I " font alloy sheets fabricate block, fiber can be carbon fiber, boron fiber, E-glass fibre, aramid fiber, resin is a liquid-state epoxy resin, and beam is that " I " font alloy sheets and composite material fabricate block are web " worker " font structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2008101369770A CN101342942B (en) | 2008-08-21 | 2008-08-21 | Disposal solidifying and forming technique for frame and outer panel skin of wing profile |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2008101369770A CN101342942B (en) | 2008-08-21 | 2008-08-21 | Disposal solidifying and forming technique for frame and outer panel skin of wing profile |
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| CN101342942A true CN101342942A (en) | 2009-01-14 |
| CN101342942B CN101342942B (en) | 2011-01-12 |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102554828A (en) * | 2011-12-28 | 2012-07-11 | 西北工业大学 | Rib assembling and positioning device |
| CN104934136A (en) * | 2015-04-27 | 2015-09-23 | 中国科学院等离子体物理研究所 | Processing technology of insulated ground shielding layer of CICC super-conducting bus |
| CN107117328A (en) * | 2016-02-25 | 2017-09-01 | 空中客车运营简化股份公司 | For the instrument that module collection is mounted in aircraft and related packaging method |
| TWI613065B (en) * | 2015-12-08 | 2018-02-01 | National Chung Shan Institute Of Science And Technology Armaments Bureau | Mold structure integrally formed by beam rib and skin and manufacturing method thereof |
| CN108177360A (en) * | 2017-12-25 | 2018-06-19 | 航天神舟飞行器有限公司 | The forming frock and its forming method of unmanned plane composite wing integral panel |
| CN109305329A (en) * | 2018-10-26 | 2019-02-05 | 上海歌尔泰克机器人有限公司 | The processing method of wing, unmanned vehicle and wing |
| CN110481811A (en) * | 2019-08-29 | 2019-11-22 | 广联航空工业股份有限公司 | A kind of unmanned plane wing entirety co-curing forming method |
| CN112032233A (en) * | 2020-08-17 | 2020-12-04 | 西安交通大学 | High-specific energy-absorbing bionic composite material structure and manufacturing method thereof |
| CN115071163A (en) * | 2022-06-22 | 2022-09-20 | 沈阳飞机工业（集团）有限公司 | Integral co-curing forming process for multi-partition-frame carbon fiber composite S-shaped air inlet channel |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107128508B (en) * | 2017-04-21 | 2019-11-15 | 陕西飞机工业（集团）有限公司 | A kind of straight wing forming method |
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2008
- 2008-08-21 CN CN2008101369770A patent/CN101342942B/en not_active Expired - Fee Related
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102554828B (en) * | 2011-12-28 | 2014-07-16 | 西北工业大学 | Rib assembling and positioning device |
| CN102554828A (en) * | 2011-12-28 | 2012-07-11 | 西北工业大学 | Rib assembling and positioning device |
| CN104934136A (en) * | 2015-04-27 | 2015-09-23 | 中国科学院等离子体物理研究所 | Processing technology of insulated ground shielding layer of CICC super-conducting bus |
| TWI613065B (en) * | 2015-12-08 | 2018-02-01 | National Chung Shan Institute Of Science And Technology Armaments Bureau | Mold structure integrally formed by beam rib and skin and manufacturing method thereof |
| CN107117328A (en) * | 2016-02-25 | 2017-09-01 | 空中客车运营简化股份公司 | For the instrument that module collection is mounted in aircraft and related packaging method |
| CN108177360B (en) * | 2017-12-25 | 2024-07-05 | 航天神舟飞行器有限公司 | Forming tool and forming method for integral wall plate of unmanned aerial vehicle composite wing |
| CN108177360A (en) * | 2017-12-25 | 2018-06-19 | 航天神舟飞行器有限公司 | The forming frock and its forming method of unmanned plane composite wing integral panel |
| CN109305329A (en) * | 2018-10-26 | 2019-02-05 | 上海歌尔泰克机器人有限公司 | The processing method of wing, unmanned vehicle and wing |
| CN110481811B (en) * | 2019-08-29 | 2022-07-05 | 广联航空工业股份有限公司 | Integral co-curing forming method for wings of unmanned aerial vehicle |
| CN110481811A (en) * | 2019-08-29 | 2019-11-22 | 广联航空工业股份有限公司 | A kind of unmanned plane wing entirety co-curing forming method |
| CN112032233A (en) * | 2020-08-17 | 2020-12-04 | 西安交通大学 | High-specific energy-absorbing bionic composite material structure and manufacturing method thereof |
| CN115071163A (en) * | 2022-06-22 | 2022-09-20 | 沈阳飞机工业（集团）有限公司 | Integral co-curing forming process for multi-partition-frame carbon fiber composite S-shaped air inlet channel |
| CN115071163B (en) * | 2022-06-22 | 2024-03-08 | 沈阳飞机工业（集团）有限公司 | Integral co-curing forming process for S-shaped air inlet channel of multi-bulkhead carbon fiber composite material |
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| CN101342942B (en) | 2011-01-12 |
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Granted publication date: 20110112 Termination date: 20110821 |