CN102555302A - 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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- CN102555302A CN102555302A CN2011104231092A CN201110423109A CN102555302A CN 102555302 A CN102555302 A CN 102555302A CN 2011104231092 A CN2011104231092 A CN 2011104231092A CN 201110423109 A CN201110423109 A CN 201110423109A CN 102555302 A CN102555302 A CN 102555302A
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Abstract
The invention relates to a process method of whole cocure shaping of a honeycomb sandwich structure of a composite material, which comprises the following steps of 1 paving the honeycomb sandwich structure; 2 paving a layer of sclausura isolation film on the honeycomb sandwich structure; 3 enabling a plurality of rectangular glass cloth to be reserved; 4 soaking the glass cloth in a glue solution to manufacture an auxiliary tool preimpregnation material; 5 placing at key groove protective positions and paving 3-5 layers of auxiliary tool preimpregnation materials along four sides in rectangle; 6 sequentially placing a layer of hole isolation film and an auxiliary ventilating martial on the upper layer of the auxiliary tool preimpregnation material; 7 enabling a tool whole of the structure to be sealed and then solidified at room temperature; and 8 sealing again to place the tool whole in a hot-press tank for solidification. The method not only is concise in processing steps, but also greatly shortens manufacture period of the honeycomb sandwich structure, and reduces manufacture cost.
Description
Technical field
The present invention relates to the whole co-curing moulding technique of a kind of composite paper wasp nest sandwich structure, be used for paper wasp nest sandwich structure is carried out whole co-curing moulding.
Background technology
Composite honeycomb sandwich structure co-curing technology is meant 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 the 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, usually the adopting process method is by two step method, three step solidification methods and the anti-sidesway co-cure method of non-skid band, adopt problem that said method exists and not enough as follows:
1) so-called two-step method: honeycomb is through the glued membrane stabilisation, and then glueds joint with panel.The two step method shortcoming: double-deck glued membrane increases honeycomb sandwich structure spare weight, simultaneously, is prone to take place weak bonding or unsticking phenomenon;
2) three step solidification methods: outer panels is solidified earlier, and the honeycomb stabilisation is gluedd joint with wainscot again.Shortcoming: panel material is in the process of bonding, because the solid state of materials at two layers different (material that solidifies earlier is hard state, and solidify the back is soft state) up and down produces stress in the process of solidifying together, causes distortion.In order to bond firmly, need before bonding, will be polished by maxxaedium, to increase adhesion strength, it is unclean that dust is detained removing surface easily in the process of polishing, and cleaning is not the main cause that causes bonding not firm only;
3) the anti-sidesway co-curing process characteristics of non-skid band are: domestic and international existing co-cure method is to make non-skid band at die edge, and honeycomb sandwich structure spare need reserve anti-skidding shop layer earlier when design.Skid resistant course is in order to prevent that the paper wasp nest from shrinking, breakking away.In operation, be difficult to realize during for shape and the anti-skidding shop of baroque processed honeycomb sandwich structure spare reservation layer, cause honeycomb slippage and contraction easily.
Summary of the invention
The technical problem that the present invention will solve provides the whole co-curing moulding technique of a kind of composite paper wasp nest sandwich structure, and this method not only procedure of processing is succinct, and can shorten the fabrication cycle of honeycomb sandwich structure spare greatly, reduces manufacturing cost.
For overcoming the above problems, concrete technical scheme of the present invention is following: the whole co-curing moulding technique of a kind of composite paper wasp nest sandwich structure may further comprise the steps:
1) laying of honeycomb sandwich structure spare:
1.1) laying several layers prepreg lower floor on frock, the paper wasp nest is bonded on the assigned address of prepreg with glued membrane then;
1.2) laying one deck glued membrane on the paper wasp nest;
1.3) continue lay several layers prepreg upper strata at the upper surface of the paper wasp nest and the prepreg lower floor of exposing all around;
2) lay one deck non-porous release film on honeycomb sandwich structure spare;
3) several are subsequent use with the rectangle glass fabric;
4) epoxy resin is become glue with the polyethylene polyamine curing agent by the 100:12 mixed, the glass fabric that step 3 is total is immersed in this glue, processes the auxiliary mould prepreg;
5) in the key groove protective position of honeycomb sandwich structure spare, along four limits, 3 ~ 5 layers of auxiliary mould prepreg of rectangular laying (8);
6) place porose barrier film of one deck and auxiliary gas permeable material successively on the upper strata of auxiliary mould prepreg;
7) the frock integral body of said structure is encapsulated after, vacuumize, vacuum is not more than-0.09MPa, the cold curing time is 8 ~ 10 hours, and then puts in the autoclave and be heating and curing once more;
8) lift auxiliary mould after the curing; After one deck and the porose barrier film of peelable cloth one deck are placed in the surface of cellular sandwich spare; Again the auxiliary mould that solidifies is placed on the porose barrier film; On auxiliary mould, lay porose barrier film of one deck and assisted ventilation material successively, encapsulate then and put into autoclave and be cured.
The whole co-curing moulding technique of this composite paper wasp nest sandwich structure adopts above-mentioned steps, and its advantage is:
1, thoroughly solves the phenomenon that there was fold on honeycomb contraction, slippage and surface when honeycomb sandwich structure spare solidified, improved honeycomb sandwich structure spare quality;
2, the manufacturing of composite honeycomb sandwich structure adopts co-curing technology can save time and manufacturing cost, prevents that effectively honeycomb sandwich structure from scrapping what the pollution of intermediate link caused;
3, effectively prevent honeycomb sandwich structure spare when repeatedly solidifying because the error that the difference of thermal stress causes the distortion of honeycomb sandwich structure spare to produce;
4, practice thrift processing cost, shorten the manufacturing cycle, the occupation rate of equipment is reduced by 3 times, effectively reduce labour cost, reduced the manufacturing cost of part;
5, the auxiliary mould material system is selected scientific and efficient, simple to operate, has solved big, the inefficient difficulty of operation easier in traditional co-curing technology, is applicable to the honeycomb sandwich structure of any complex profile.
Description of drawings
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, the whole co-curing moulding technique of a kind of composite paper wasp nest sandwich structure may further comprise the steps:
1) laying of honeycomb sandwich structure spare:
1.1) laying prepreg lower floor 2 on frock 1, laying is 16 layers altogether, paper wasp nest 4 is bonded on the assigned address of prepreg with glued membrane 3 then;
1.2) on paper wasp nest 4, lay one deck glued membrane 3, the above-mentioned glued membrane trade mark is J-116A;
1.3) continuing lay prepreg upper strata 6 at the upper surface of the paper wasp nest 4 and the prepreg lower floor 2 of exposing all around, laying is 16 layers altogether, and wherein the trade mark of prepreg levels is the CF3031/BA9916-II;
2) lay one deck non-porous release film 7 on honeycomb sandwich structure spare;
3) several are subsequent use with the rectangle glass fabric, and the trade mark of glass fabric is PPGW-R-800-GSM;
4) epoxy resin E51 is become glue with the polyethylene polyamine curing agent by the 100:12 mixed, the glass fabric that step 3 is total is immersed in this glue, processes auxiliary mould prepreg 8;
5) as shown in Figure 2, in the key groove protective position of honeycomb sandwich structure spare, lay along 3 ~ 5 layers of auxiliary mould prepreg of the rectangular laying in four limits 8, need in one hour, to accomplish;
6) place porose barrier film 7 of one deck and auxiliary gas permeable material 10 successively on the upper strata of auxiliary mould prepreg 8, the trade mark of hole barrier film 7 is A4000 P3, and auxiliary gas permeable material 10 is the airfelt of AIRWEAVE N-10 for the trade mark;
7) the frock integral body of said structure is encapsulated after, vacuumize, vacuum is not more than-0.09MPa, the cold curing time is 8 ~ 10 hours, solidifies back auxiliary mould prepreg 8 moulding that is cured earlier;
8) lift auxiliary mould after the curing, after one deck and the porose barrier film of peelable cloth one deck are placed in the surface of cellular sandwich spare, again the auxiliary mould that solidifies is placed on the porose barrier film; On auxiliary mould, lay porose barrier film of one deck and assisted ventilation material successively; Encapsulate then and put into autoclave and be cured, auxiliary mould that prevents like this to have cured and the adhesion between the cellular sandwich spare influence the profile of cellular sandwich spare; Its cure parameter is 180 ℃ of temperature, and pressure is 0.6MPa.Auxiliary mould elder generation curing molding like this; For in the post bake curing paper wasp nest 4 having been played the effect of locating, the material of auxiliary mould is close with the material of prepreg simultaneously, so after being heated; Make the stressed even of paper wasp nest, thereby avoided the shortcoming that the paper wasp nest breaks away and subsides in the traditional handicraft.
The whole co-curing moulding technique of this composite paper wasp nest sandwich structure technology applicability is strong, is fit to make the honeycomb sandwich structure spare of random appearance, can guarantee the accurate manufacturing of honeycomb sandwich structure honeycomb sandwich structure spare profile and internal soundness.This process operation is succinct, simple to operate, only need carry out autoclave one time, has reduced the various possibility that causes honeycomb sandwich structure spare to be scrapped of middle operation, has saved a large amount of manpower and materials, raises the efficiency, and has created considerable economic.
Claims (1)
1. the whole co-curing moulding technique of a composite paper wasp nest sandwich structure is characterized in that may further comprise the steps:
1) laying of honeycomb sandwich structure spare:
1.1) go up laying several layers prepreg lower floor (2) in frock (1), use glued membrane (3) that paper wasp nest (4) is bonded on the assigned address of prepreg then;
1.2) go up laying one deck glued membrane (3) at paper wasp nest (4);
1.3) continue lay several layers prepreg upper strata (6) at the upper surface of the paper wasp nest (4) and the prepreg lower floor (2) of exposing all around;
2) lay one deck non-porous release film (7) on honeycomb sandwich structure spare;
3) several are subsequent use with the rectangle glass fabric;
4) epoxy resin is become glue with the polyethylene polyamine curing agent by the 100:12 mixed, the glass fabric that step 3 is total is immersed in this glue, processes auxiliary mould prepreg (8);
5) in the key groove protective position of honeycomb sandwich structure spare, along four limits, 3 ~ 5 layers of auxiliary mould prepreg of rectangular laying (8);
6) place porose barrier film of one deck (9) and auxiliary gas permeable material (10) successively on the upper strata of auxiliary mould prepreg (8);
7) the frock integral body of said structure is encapsulated after, vacuumize, vacuum is not more than-0.09MPa, the cold curing time is 8 ~ 10 hours;
8) lift auxiliary mould after the curing; After peelable cloth of one deck and the porose barrier film of one deck are placed in the surface of cellular sandwich spare; Again the auxiliary mould that solidifies is placed on the porose barrier film; On auxiliary mould, lay porose barrier film of one deck and assisted ventilation material successively, encapsulate then and put into autoclave and be cured.
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103935050A (en) * | 2014-05-14 | 2014-07-23 | 北京航空航天大学 | Sandwiched structure forming process for preventing slippage and collapse of thick honeycombs |
| 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 |
| 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 |
| CN105408096A (en) * | 2013-07-26 | 2016-03-16 | 里尔喷射机公司 | Composite material incorporating water ingress barrier |
| 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 |
| 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 |
| 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 |
| CN110425410A (en) * | 2019-05-29 | 2019-11-08 | 陕西飞机工业（集团）有限公司 | A kind of composite material cellular board sandwich layer dampproof method |
| CN112829161A (en) * | 2021-01-07 | 2021-05-25 | 中国航空制造技术研究院 | Foaming glue filling method for composite material honeycomb sandwich structure |
| CN114919241A (en) * | 2022-05-10 | 2022-08-19 | 宁波曙翔新材料股份有限公司 | Box-shaped composite material forming process suitable for paper honeycombs with large thickness |
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| CN106757006B (en) * | 2016-12-29 | 2019-12-27 | 中航沈飞民用飞机有限责任公司 | Repair method for anti-skid belt |
| CN110103483B (en) * | 2019-04-18 | 2021-08-03 | 成都飞机工业（集团）有限责任公司 | Honeycomb core splicing method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101426830A (en) * | 2006-04-25 | 2009-05-06 | 横滨橡胶株式会社 | Epoxy resin composition for fiber-reinforced composite material |
| 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 |
| CN102009501A (en) * | 2009-09-08 | 2011-04-13 | 上海卫星工程研究所 | Enhanced honeycomb sandwich structural slab and production method thereof |
| 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 |
-
2011
- 2011-12-16 CN CN201110423109.2A patent/CN102555302B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101426830A (en) * | 2006-04-25 | 2009-05-06 | 横滨橡胶株式会社 | Epoxy resin composition for fiber-reinforced composite material |
| CN102009501A (en) * | 2009-09-08 | 2011-04-13 | 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 |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105408096A (en) * | 2013-07-26 | 2016-03-16 | 里尔喷射机公司 | Composite material incorporating water ingress barrier |
| US10220593B2 (en) | 2013-07-26 | 2019-03-05 | Learjet Inc. | Composite material incorporating water ingress barrier |
| CN103935050A (en) * | 2014-05-14 | 2014-07-23 | 北京航空航天大学 | Sandwiched structure forming process for preventing slippage and collapse of thick honeycombs |
| 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 |
| CN110425410A (en) * | 2019-05-29 | 2019-11-08 | 陕西飞机工业（集团）有限公司 | A kind of composite material cellular board sandwich layer dampproof method |
| CN112829161A (en) * | 2021-01-07 | 2021-05-25 | 中国航空制造技术研究院 | Foaming glue filling method for composite material honeycomb sandwich structure |
| CN114919241A (en) * | 2022-05-10 | 2022-08-19 | 宁波曙翔新材料股份有限公司 | Box-shaped composite material forming process suitable for paper honeycombs with large thickness |
| CN114919241B (en) * | 2022-05-10 | 2024-04-16 | 宁波曙翔新材料股份有限公司 | Box-shaped composite material forming process suitable for honeycomb containing large-thickness paper |
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