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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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 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)
1. a process method of whole cocure shaping of honeycomb sandwich structure of composite material, is characterized in that comprising the following steps:
1) laying of honeycomb sandwich structure part:
1.1) in the upper some layers of prepreg lower floor of laying (2) of frock (1), then use glued membrane (3) that paper honeycomb (4) is bonded on the assigned address of prepreg;
1.2) at the upper one deck glued membrane (3) of laying of paper honeycomb (4);
1.3) upper surface of the prepreg lower floor (2) of exposing in paper honeycomb (4) and surrounding continues to lay some layers of prepreg upper strata (6);
2) lay one deck non-porous release film (7) 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 glass fabric in step 3 is immersed in this glue, make auxiliary mould prepreg (8);
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 (8), place successively the porose barrier film of one deck (9) and auxiliary gas permeable material (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;
8) lift the auxiliary mould after solidifying, on the surface of honeycomb sandwich piece, place after the peelable cloth of one deck and the porose barrier film of 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.
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| 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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| 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 |
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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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| 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 |
| 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 |
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