CN102555302B - Process method of whole cocure shaping of honeycomb sandwich structure of composite material - Google Patents
Process method of whole cocure shaping of honeycomb sandwich structure of composite material Download PDFInfo
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- CN102555302B CN102555302B CN201110423109.2A CN201110423109A CN102555302B CN 102555302 B CN102555302 B CN 102555302B CN 201110423109 A CN201110423109 A CN 201110423109A CN 102555302 B CN102555302 B CN 102555302B
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- Prior art keywords
- honeycomb sandwich
- prepreg
- honeycomb
- deck
- auxiliary mould
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- 210000003660 Reticulum Anatomy 0.000 title claims abstract description 66
- 238000000034 methods Methods 0.000 title claims abstract description 21
- 239000002131 composite materials Substances 0.000 title claims abstract description 14
- 238000007493 shaping process Methods 0.000 title claims abstract description 10
- 239000000463 materials Substances 0.000 claims abstract description 17
- 239000010410 layers Substances 0.000 claims abstract description 14
- 239000004744 fabrics Substances 0.000 claims abstract description 12
- 239000011521 glasses Substances 0.000 claims abstract description 9
- 239000003292 glue Substances 0.000 claims abstract description 7
- 230000001681 protective Effects 0.000 claims abstract description 4
- 239000007789 gases Substances 0.000 claims description 4
- 239000004698 Polyethylene (PE) Substances 0.000 claims description 3
- 239000003795 chemical substances by application Substances 0.000 claims description 3
- 239000003822 epoxy resins Substances 0.000 claims description 3
- 229920000768 polyamines Polymers 0.000 claims description 3
- 229920000647 polyepoxides Polymers 0.000 claims description 3
- -1 polyethylene Polymers 0.000 claims description 3
- 229920000573 polyethylenes Polymers 0.000 claims description 3
- 238000009423 ventilation Methods 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 11
- 238000007711 solidification Methods 0.000 abstract description 4
- 238000002955 isolation Methods 0.000 abstract 2
- 238000007789 sealing Methods 0.000 abstract 1
- 238000002791 soaking Methods 0.000 abstract 1
- 238000000465 moulding Methods 0.000 description 4
- 230000003019 stabilising Effects 0.000 description 2
- 238000004140 cleaning Methods 0.000 description 1
- 239000000428 dust Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering processes Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000005498 polishing Methods 0.000 description 1
- 239000007787 solids Substances 0.000 description 1
Abstract
Description
Technical field
The present invention relates to a kind of process method of whole cocure shaping of honeycomb sandwich structure of composite material, for paper honeycomb sandwich structure being carried out to whole co-curing moulding.
Background technology
Composite honeycomb sandwich structure co-curing technique refers to the manufacturing process that the splicing of composite material solidification moulding and panel and honeycomb is carried out simultaneously.The Composite Sandwich structure that contains wedge shape honeycomb, the glued membrane viscosity between honeycomb and covering is low at a certain temperature, and the lateral pressure that briquetting pressure produces on honeycomb causes the whole lateral sliding of honeycomb, causes part to scrap.
At present, adopting process method is by two step method, three step solidification methods and the anti-sidesway co-cure method of non-skid band conventionally, and the problem and the deficiency that adopt said method to exist are as follows:
1) so-called two-step method: honeycomb is through glued membrane stabilisation, and then glued joint with panel., meanwhile, easily there is weak bonding or unsticking phenomenon in two step method shortcoming: double-deck glued membrane increases honeycomb sandwich structure part weight;
2) three step solidification methods: outer panels is first solidified, honeycomb stabilisation, then glued joint with wainscot.Shortcoming: panel material, in the process of bonding, due to the solid state of upper and lower two layers of material different (first curing material is hard state, the rear curing soft state that is), produces stress in curing process together, causes distortion.In order to bond firmly, need to before bonding, will be polished by maxxaedium, to increase adhesion strength, it is unclean that in the process of polishing, dust is easily detained removing surface, and cleaning is not the main cause that causes bonding not firm only;
3) the anti-sidesway co-curing of non-skid band process feature is: domestic and international existing co-cure method is to make non-skid band at die edge, and honeycomb sandwich structure part need to first reserve anti-skidding laying when design.Skid resistant course is in order to prevent that paper honeycomb from shrinking, breakking away.During for shape and the reserved anti-skidding laying of baroque processed honeycomb sandwich structure part, in operation, be difficult to realize, easily cause honeycomb slippage and contraction.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of process method of whole cocure shaping of honeycomb sandwich structure of composite material, and the method not only procedure of processing is succinct, and can greatly shorten the fabrication cycle of honeycomb sandwich structure part, reduces manufacturing cost.
For overcoming the above problems, concrete technical scheme of the present invention is as follows: a kind of process method of whole cocure shaping of honeycomb sandwich structure of composite material, comprises the following steps:
1) laying of honeycomb sandwich structure part:
1.1) some layers of prepreg lower floor of laying in frock, are then bonded at paper honeycomb on the assigned address of prepreg with glued membrane;
1.2) on paper honeycomb, lay one deck glued membrane;
1.3) upper surface of the prepreg lower floor of exposing in paper honeycomb and surrounding continues to lay some layers of prepreg upper strata;
2) lay one deck non-porous release film on honeycomb sandwich structure part;
3) by rectangle glass fabric, several are standby;
4) epoxy resin and polyethylene polyamine curing agent are mixed into glue in 100:12 ratio, the total glass fabric of step 3 is immersed in this glue, make auxiliary mould prepreg;
5) in the key groove protective position of honeycomb sandwich structure part, along four limit 3 ~ 5 layers of auxiliary mould prepreg of rectangular laying (8);
6) on the upper strata of auxiliary mould prepreg, place successively the porose barrier film of one deck and auxiliary gas permeable material;
7) after the frock integral body of said structure is encapsulated, vacuumize, be not more than-0.09MPa of vacuum, the cold curing time is 8 ~ 10 hours, and then puts in autoclave and be again heating and curing;
8) lift the auxiliary mould after solidifying, on the surface of honeycomb sandwich piece, place after one deck and the porose barrier film of peelable cloth one deck, again curing auxiliary mould is placed on porose barrier film, on auxiliary mould, lay successively the porose barrier film of one deck and assisted ventilation material, then encapsulate and put into autoclave and be cured.
This process method of whole cocure shaping of honeycomb sandwich structure of composite material adopts above-mentioned steps, and its advantage is:
1, thoroughly solve the phenomenon that when honeycomb sandwich structure part solidifies, there is fold on honeycomb contraction, slippage and surface, improved honeycomb sandwich structure part quality;
2, the manufacture of composite honeycomb sandwich structure adopts co-curing technique can save time and manufacturing cost, and what effectively prevent that honeycomb sandwich structure from causing in the pollution of intermediate link scraps;
3, effectively prevent that honeycomb sandwich structure part from causing the error of the distortion generation of honeycomb sandwich structure part when repeatedly solidifying due to the difference of thermal stress;
4, save processing cost, shorten the manufacturing cycle, the occupation rate of equipment is reduced to 3 times, effectively reduce labour cost, reduced the manufacturing cost of part;
5, the selection of auxiliary mould material system is scientific and efficient, simple to operate, has solved large, the inefficient difficulty of operation easier in traditional co-curing technique, is applicable to the honeycomb sandwich structure of any complex profile.
Accompanying drawing explanation
Fig. 1 is for making the structural representation of auxiliary mould.
Fig. 2 is the structural representation of auxiliary mould.
The specific embodiment
As shown in Figure 1, a kind of process method of whole cocure shaping of honeycomb sandwich structure of composite material, comprises the following steps:
1) laying of honeycomb sandwich structure part:
1.1) laying prepreg lower floor 2 in frock 1, laying is 16 layers altogether, then with glued membrane 3, paper honeycomb 4 is bonded on the assigned address of prepreg;
1.2) on paper honeycomb 4, lay one deck glued membrane 3, the above-mentioned glued membrane trade mark is J-116A;
1.3) upper surface of the prepreg lower floor 2 of exposing in paper honeycomb 4 and surrounding continues to lay prepreg upper strata 6, and laying is 16 layers altogether, and wherein the trade mark of prepreg levels is CF3031/BA9916-II;
2) lay one deck non-porous release film 7 on honeycomb sandwich structure part;
3) by rectangle glass fabric, several are standby, and the trade mark of glass fabric is PPGW-R-800-GSM;
4) epoxy resin E51 and polyethylene polyamine curing agent are mixed into glue in 100:12 ratio, the total glass fabric of step 3 is immersed in this glue, make auxiliary mould prepreg 8;
5) as shown in Figure 2, in the key groove protective position of honeycomb sandwich structure part, along 3 ~ 5 layers of auxiliary mould prepreg of the four rectangular layings in limit 8, lay, need in one hour, complete;
6) on the upper strata of auxiliary mould prepreg 8, place successively the porose barrier film 7 of one deck and auxiliary gas permeable material 10, the trade mark of hole barrier film 7 is A4000 P3, auxiliary gas permeable material 10 for the trade mark be the airfelt of AIRWEAVE N-10;
7) after the frock integral body of said structure is encapsulated, vacuumize, be not more than-0.09MPa of vacuum, the cold curing time is 8 ~ 10 hours, auxiliary mould prepreg 8 moulding that is first cured after solidifying;
8) lift the auxiliary mould after solidifying, on the surface of honeycomb sandwich piece, place after one deck and the porose barrier film of peelable cloth one deck, again curing auxiliary mould is placed on porose barrier film, on auxiliary mould, lay successively the porose barrier film of one deck and assisted ventilation material, then encapsulate and put into autoclave and be cured, prevent like this auxiliary mould that has cured and the adhesion between honeycomb sandwich piece, affect the profile of honeycomb sandwich piece, its cure parameter is 180 ℃ of temperature, and pressure is 0.6MPa.The first curing molding of auxiliary mould like this, for post bake has played the effect of location to paper honeycomb 4 in solidifying, the material of auxiliary mould is close with the material of prepreg simultaneously, therefore after being heated, make the stressed even of paper honeycomb, thereby avoided the shortcoming that in traditional handicraft, paper honeycomb breaks away and subsides.
This process method of whole cocure shaping of honeycomb sandwich structure of composite material technique applicability is strong, is applicable to making the honeycomb sandwich structure part of random appearance, can guarantee the accurate manufacture of honeycomb sandwich structure honeycomb sandwich structure part profile and internal soundness.This process operation is succinct, simple to operate, only need to carry out autoclave one time, has reduced the various possibility that causes honeycomb sandwich structure part to be scrapped of middle operation, has saved a large amount of manpower and materials, raises the efficiency, and has created considerable economic benefit.
Claims (1)
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| Application Number | Priority Date | Filing Date | Title |
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| CN201110423109.2A CN102555302B (en) | 2011-12-16 | 2011-12-16 | Process method of whole cocure shaping of honeycomb sandwich structure of composite material |
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| CN201110423109.2A CN102555302B (en) | 2011-12-16 | 2011-12-16 | Process method of whole cocure shaping of honeycomb sandwich structure of composite material |
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| Publication Number | Publication Date |
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| CN102555302A CN102555302A (en) | 2012-07-11 |
| CN102555302B true CN102555302B (en) | 2014-01-22 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106757006A (en) * | 2016-12-29 | 2017-05-31 | 中航沈飞民用飞机有限责任公司 | New-type antiskid band repair method |
| CN110103483A (en) * | 2019-04-18 | 2019-08-09 | 成都飞机工业（集团）有限责任公司 | A kind of honeycomb core joining method |
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| CN105408096A (en) * | 2013-07-26 | 2016-03-16 | 里尔喷射机公司 | Composite material incorporating water ingress barrier |
| CN103935050B (en) * | 2014-05-14 | 2016-06-08 | 北京航空航天大学 | A kind of sandwich structure moulding technique preventing thick honeycomb sliding from subsiding |
| CN104139531A (en) * | 2014-06-27 | 2014-11-12 | 中航飞机股份有限公司西安飞机分公司 | Method for improving adhesion property of prepreg and fixture when composite material is automatically belt-laid |
| CN105538743A (en) * | 2014-10-28 | 2016-05-04 | 哈尔滨飞机工业集团有限责任公司 | Honeycomb second pre-molding method |
| CN104875398A (en) * | 2015-06-17 | 2015-09-02 | 沈阳飞机工业（集团）有限公司 | Manufacturing method of large-curvature sandwich structure special-shaped part made of composite material |
| CN105479778A (en) * | 2015-11-26 | 2016-04-13 | 中国航空工业集团公司基础技术研究院 | Flexible pressure pad for hot press molding of parts with complex profiles |
| CN108000895A (en) * | 2017-11-02 | 2018-05-08 | 哈尔滨飞机工业集团有限责任公司 | A kind of method for preventing from producing fold when honeycomb sandwich construction chamfering from curing |
Family Cites Families (5)
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| JP4141479B2 (en) * | 2006-04-25 | 2008-08-27 | 横浜ゴム株式会社 | Epoxy resin composition for fiber reinforced composite materials |
| CN102009501B (en) * | 2009-09-08 | 2013-11-27 | 上海卫星工程研究所 | Enhanced honeycomb sandwich structural slab and production method thereof |
| CN101797822A (en) * | 2010-03-29 | 2010-08-11 | 王韬 | Novel fiber reinforced cellular board and preparation method thereof |
| CN101913250A (en) * | 2010-08-17 | 2010-12-15 | 沈阳飞机工业（集团）有限公司 | Rudder wall plate molding process |
| CN102218828A (en) * | 2011-05-27 | 2011-10-19 | 常州市宏发纵横新材料科技股份有限公司 | Method for preparing continuous fiber multiaxial fabric reinforced thermoplastic composite material |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106757006A (en) * | 2016-12-29 | 2017-05-31 | 中航沈飞民用飞机有限责任公司 | New-type antiskid band repair method |
| CN110103483A (en) * | 2019-04-18 | 2019-08-09 | 成都飞机工业（集团）有限责任公司 | A kind of honeycomb core joining method |
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| Publication number | Publication date |
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| CN102555302A (en) | 2012-07-11 |
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