CN104842593A - Carbon fiber honeycomb structure and preparation method therefor - Google Patents
Carbon fiber honeycomb structure and preparation method therefor Download PDFInfo
- Publication number
- CN104842593A CN104842593A CN201510150581.1A CN201510150581A CN104842593A CN 104842593 A CN104842593 A CN 104842593A CN 201510150581 A CN201510150581 A CN 201510150581A CN 104842593 A CN104842593 A CN 104842593A
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- Prior art keywords
- carbon fiber
- honeycomb
- preparation
- mould
- honeycomb structure
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- Granted
Links
- 229920000049 Carbon (fiber) Polymers 0.000 title claims abstract description 54
- 239000004917 carbon fiber Substances 0.000 title claims abstract description 54
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 title claims abstract description 54
- 238000002360 preparation method Methods 0.000 title claims abstract description 28
- 238000000034 method Methods 0.000 claims abstract description 13
- 239000000853 adhesive Substances 0.000 claims abstract description 8
- 230000001070 adhesive effect Effects 0.000 claims abstract description 8
- 238000003825 pressing Methods 0.000 claims abstract description 7
- 239000003822 epoxy resin Substances 0.000 claims abstract description 6
- 229920000647 polyepoxide Polymers 0.000 claims abstract description 6
- 230000008569 process Effects 0.000 claims abstract description 6
- 238000000465 moulding Methods 0.000 claims description 11
- 239000000463 material Substances 0.000 claims description 9
- OAICVXFJPJFONN-UHFFFAOYSA-N Phosphorus Chemical compound [P] OAICVXFJPJFONN-UHFFFAOYSA-N 0.000 claims description 5
- 239000007767 bonding agent Substances 0.000 claims description 5
- 229910052698 phosphorus Inorganic materials 0.000 claims description 5
- 239000011574 phosphorus Substances 0.000 claims description 5
- 238000007493 shaping process Methods 0.000 claims description 5
- 238000001816 cooling Methods 0.000 claims description 4
- 239000012528 membrane Substances 0.000 claims description 4
- 238000010926 purge Methods 0.000 claims description 4
- 229910000838 Al alloy Inorganic materials 0.000 claims description 3
- 229910000831 Steel Inorganic materials 0.000 claims description 3
- 239000011248 coating agent Substances 0.000 claims description 3
- 238000000576 coating method Methods 0.000 claims description 3
- 239000002356 single layer Substances 0.000 claims description 3
- 239000010959 steel Substances 0.000 claims description 3
- 239000011230 binding agent Substances 0.000 claims description 2
- 238000006664 bond formation reaction Methods 0.000 claims description 2
- 239000003795 chemical substances by application Substances 0.000 claims description 2
- 238000010438 heat treatment Methods 0.000 claims description 2
- 238000007731 hot pressing Methods 0.000 claims description 2
- 229910052799 carbon Inorganic materials 0.000 abstract description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 abstract description 2
- 230000003139 buffering effect Effects 0.000 abstract description 2
- 239000002131 composite material Substances 0.000 abstract description 2
- 230000000694 effects Effects 0.000 abstract description 2
- 239000011162 core material Substances 0.000 abstract 1
- 230000007547 defect Effects 0.000 abstract 1
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 description 4
- 238000007711 solidification Methods 0.000 description 3
- 230000008023 solidification Effects 0.000 description 3
- 230000001413 cellular effect Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 239000004576 sand Substances 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 239000002390 adhesive tape Substances 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005034 decoration Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 230000014759 maintenance of location Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
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- Laminated Bodies (AREA)
Abstract
The present invention relates to the technical field of composite materials, particularly a carbon fiber honeycomb structure. The carbon fiber honeycomb structure comprises a plurality of honeycomb sub parts in shapes of continuous semi-hexagons; the plurality of honeycomb sub parts are sequentially arranged in correspondence; an adhesive is coated to overlapped adhesion surfaces to be fixedly adhered to form the honeycomb structure with a hexagonal cross section; a carbon fiber prepreg with a carbon amount over 90% is subjected to an autoclave process or mold pressing process to prepare the honeycomb sub parts; the adhesive is an epoxide resin adhesive or a rubber film. Compared with the conventional honeycomb core material, the comprehensive performance of the carbon fiber honeycomb structure is outstanding, the weight is less, the specific intensity is high, the impact resistant performance is excellent, and the buffering and energy absorbing effects are remarkable. The present invention further provides a preparation method of the carbon fiber honeycomb structure, and overcomes the defect of complex preparation process of the conventional carbon fiber honeycomb structure.
Description
Technical field
The present invention relates to technical field of composite materials, particularly a kind of carbon fiber honeycomb, the present invention additionally provides the preparation method of this kind of carbon fiber honeycomb simultaneously.
Background technology
Sandwich material based on comb core is widely used in the fields such as Aero-Space, automobile, decoration, is used for improving intensity, rigidity, strengthens impact resistance, and weight reduction simultaneously reduces noise.
In comb core, common are paper honeycomb core, carbon fiber paper honeycomb, metal honeycomb core etc.The all each tool pluses and minuses of its performance in existing comb core, as paper honeycomb core and carbon fiber paper honeycomb lightweight, but intensity, hardness is general, and specific strength is low, shock resistance weak effect; Metal honeycomb core intensity is high, and hardness is high, but heavier-weight, and specific strength is general.Therefore the comb core providing a kind of combination property superior is necessary.
Carbon fiber honeycomb is lightweight, energy absorption performance is outstanding, and in automobile energy-absorbing structure, application prospect is extensive.Prepare the single hexagon pipe fitting of the general first pultrusion of fibers honeycomb at present, then become carbon fiber by many independent pipe fittings are bonding, the method operation is too complicated, single tube be shaped and bonding workload large.Therefore, the carbon fiber comb core preparation method that simple possible is provided is necessary.
Summary of the invention
The present invention is in order to solve the various general issues that current existing comb core exists and a kind of carbon fiber honeycomb provided.
For reaching above-mentioned functions, technical scheme provided by the invention is:
A kind of carbon fiber honeycomb, it is characterized in that: comprise multiple honeycomb component with continuous semi-hexagon shape shape, multiple described honeycomb component is corresponding in turn to arrangement and forms cross section at the adhesive surface place applied adhesive fixed bonding overlapped is hexagonal honeycomb, wherein:
Described honeycomb component, adopts the carbon fiber prepreg of phosphorus content more than 90% to be made by autoclave technique or mould pressing process;
Described binding agent, adopts epoxy resin bonding agent or glued membrane.
The present invention additionally provides the preparation method of above-mentioned carbon fiber honeycomb simultaneously, comprises the following steps:
Step S1, the carbon fiber prepreg calculated is cut into the size of requirement, gets the required number of plies ready;
Step S2, to mould and die preheating, coating release agent, is compacted in mould by superimposed from level to level for the carbon fiber prepreg got ready, repaves upper auxiliary material, after completing the preparation before mould, put in former according to technological requirement:
Step S3, technological parameter is set after, start former carry out hot pressing;
After step S4, cooling, the demoulding obtains honeycomb component, to mould purge;
Step S5, repetition step S1 ~ S4, until the honeycomb component of obtained requirement;
Step S6, by the carbon fiber honeycomb core structures material of obtained semi-hexagonal described honeycomb component corresponding bonding formation hexagonal shape between two successively in fixture;
Step S7, carry out machine-shaping to described carbon fiber honeycomb core structures material, sheet is cut and can be obtained carbon fiber honeycomb.
Preferably, the phosphorus content of described carbon fiber prepreg is more than 90%.
Preferably, the computing formula of required number of plies n is:
N=t/h, described t represents the molding thickness of honeycomb component, and described h represents the thickness in monolayer of carbon fiber prepreg.
Preferably, described former is autoclave, and described technological parameter is:
Temperature parameter is for heating to 140 ~ 160 DEG C, and constant temperature time is 60 ~ 80min, cools to 60 ~ 80 DEG C, and the time is 10 ~ 30min, and pressure parameter is 0.5 ~ 1.0MPa.
Preferably, described former is moulding press, and described technological parameter is:
Molding temperature is 120 ~ 180 DEG C, and the time is 40 ~ 80min, and pressure is 0.5 ~ 0.7Mpa.
Preferably, the cross section of described mould is continuous semi-hexagon shape shape.
Preferably, described mould adopts aluminium alloy or mould steel to make.
Beneficial effect of the present invention is: carbon fiber honeycomb of the present invention with existing comb core compare have lightweight, specific strength is high, shock resistance is good, buffering energy-absorbing successful, can be widely used in the fields such as auto industry, sports equipment, aerospace, fire-fighting.
Accompanying drawing explanation
Fig. 1 is the structural representation of honeycomb component
Fig. 2 is the bonding structural representation of two honeycomb components;
Fig. 3 is structural representation of the present invention;
Fig. 4 is the structural representation of the mould that autoclave technique adopts;
Fig. 5 is the structural representation of the mould that mould pressing process adopts.
Detailed description of the invention
Below in conjunction with accompanying drawing 1 to accompanying drawing 5, the present invention is further elaborated:
A kind of carbon fiber honeycomb as shown in Figure 1 to Figure 3, comprise multiple honeycomb component 1 with continuous semi-hexagon shape shape, multiple described honeycomb component 1 be corresponding in turn to arrangement and overlap adhesive surface 11 place epoxy resin coating class bonding agent or glued membrane, it is hexagonal honeycomb that fixed bonding forms cross section, in the present invention, honeycomb component 1, adopts the carbon fiber prepreg of phosphorus content more than 90% heat to be made by autoclave technique or mould pressing process.
Carbon fiber honeycomb of the present invention passes through with preparation method, prepares and obtains:
Preparation method one:
The autoclave technique that this preparation method adopts, comprises the following steps:
Step S1, the carbon fiber prepreg calculated is cut into the size of requirement, get required number of plies n, n=t/h ready, wherein t represents the molding thickness of shaping rear honeycomb component 1, and h represents the thickness in monolayer of carbon fiber prepreg;
Step S2, be compacted to superimposed from level to level for the carbon fiber prepreg got ready the mould 2 with tongue and groove being preheating to 70 DEG C, as shown in Figure 4, the cross section of mould 2 is continuous semi-hexagon shape shape, order from inside to outside spreads barrier film, ventilative sticky parcel successively, mould 2 loads in vacuum bag, put it into again in autoclave, then vacuum bag is vacuumized;
In S3, autoclave, temperature parameter is set to heat to 150 DEG C, and temperature retention time is 60min, cools to 75 DEG C, and the time is 30min, and pressure parameter is set to 0.7MPa, starts autoclave;
S4, from autoclave, take out cooling and demolding after mould 2 obtain finished product, mould 2 purge, reach the requirement of next finished product of preparation.
S5, repetition step S1 ~ S4, the honeycomb component 1 in the semi-hexagon shape cross section as shown in Figure 1 of obtained some;
S6, by the sand papering of honeycomb component 1 bonding plane, then to clean with acetone;
S7, use epoxy resin bonding agent bonding between two at normal temperatures semi-hexagonal honeycomb component 1, form the carbon fiber honeycomb of hexagonal shape after solidification, as shown in Figures 2 and 3;
S8, carry out machine-shaping to profile, sheet is switched to the carbon fiber cellular structural material of desired height, as shown in Figure 3.
In this preparation method, mould 2 can the mould made of aluminium alloy or mould steel.Preparation method two:
Change preparation method one step S7, semi-hexagonal honeycomb component 1 is bonding between two with epoxy resin bonding agent at 120 DEG C of temperature, form the carbon fiber honeycomb of hexagonal shape after solidification.
Preparation method three:
The technique of the moulding press mold pressing that this preparation method adopts, comprises the following steps:
S1, the carbon fiber prepreg calculated is cut into the size of requirement, gets the required number of plies ready;
S2, as shown in Figure 5, will be taped against in former 3 after the carbon cloth 5 got ready from level to level superimposed compacting, by former 3 and formpiston 4 matched moulds, entirety is put into moulding press, setting molding temperature be 150 DEG C, and the time is 60min, and pressure is 0.5mpa, carries out mold pressing;
S3, from moulding press, take out mould after cooling and demolding obtain honeycomb component 1, mould purge, reach preparation next finished product requirement.
S4, repetition step S1 ~ S3, the honeycomb component 1 of obtained some, the honeycomb component 1 in the semi-hexagon shape cross section as shown in Figure 1 of obtained some;
S5, to the sand papering of honeycomb component 1 bonding plane, then to clean with acetone;
S6, stick glued membrane at honeycomb in the bonding plane of part 1, honeycomb component 1 is bonding between two, and compress, fix with adhesive tape, be put in autoclave, temperature is not set to 120 DEG C, and the time is 20min, is cured;
Carry out machine-shaping to profile after S7, solidification, sheet is switched to the carbon fiber cellular structural material of desired height.
As shown in Figure 5, former 3 and formpiston 4 have corresponding continuous semi-hexagon shape shape.
It should be noted that in above-mentioned preparation method one to preparation method three, the selection of the technological parameter when producing is a preferably scheme, the producer can select other corresponding technological parameter according to the need of production of reality, if do not particularly point out, the general means that technological means used in case study on implementation is familiar with by those skilled in the art, all raw material is all commercially on sale.
The above embodiment, just preferred embodiments of the present invention, be not limit practical range of the present invention, therefore all equivalences done according to structure, feature and the principle described in the present patent application the scope of the claims change or modify, and all should be included in patent claim of the present invention.
Claims (8)
1. a carbon fiber honeycomb, it is characterized in that: comprise multiple honeycomb component with continuous semi-hexagon shape shape, multiple described honeycomb component is corresponding in turn to arrangement and forms cross section at the adhesive surface place applied adhesive fixed bonding overlapped is hexagonal honeycomb, wherein:
Described honeycomb component, adopts the carbon fiber prepreg of phosphorus content more than 90% to be made by autoclave technique or mould pressing process;
Described binding agent, adopts epoxy resin bonding agent or glued membrane.
2. a preparation method for carbon fiber honeycomb as claimed in claim 1, is characterized in that, comprise the following steps:
Step S1, the carbon fiber prepreg calculated is cut into the size of requirement, gets the required number of plies ready;
Step S2, to mould and die preheating, coating release agent, is compacted in mould by superimposed from level to level for the carbon fiber prepreg got ready, repaves upper auxiliary material, after completing the preparation before mould, put in former according to technological requirement;
Step S3, technological parameter is set after, start former carry out hot pressing;
After step S4, cooling, the demoulding obtains honeycomb component, to mould purge;
Step S5, repetition step S1 ~ S4, until the honeycomb component of obtained requirement;
Step S6, by the carbon fiber honeycomb core structures material of obtained semi-hexagonal described honeycomb component corresponding bonding formation hexagonal shape between two successively in fixture;
Step S7, carry out machine-shaping to described carbon fiber honeycomb core structures material, sheet is cut and can be obtained carbon fiber honeycomb.
3. the preparation method of carbon fiber honeycomb as claimed in claim 2, is characterized in that: the phosphorus content of described carbon fiber prepreg is more than 90%.
4. the preparation method of carbon fiber honeycomb as claimed in claim 2, is characterized in that: the computing formula of required number of plies n is:
N=t/h, described t represents molding thickness, and described h represents the thickness in monolayer of carbon fiber prepreg.
5. the preparation method of carbon fiber honeycomb as claimed in claim 2, is characterized in that: described former is autoclave, and described technological parameter is:
Temperature parameter is for heating to 140 ~ 160 DEG C, and constant temperature time is 60 ~ 80min, cools to 60 ~ 80 DEG C, and the time is 10 ~ 30min, and pressure parameter is 0.5 ~ 1.0MPa.
6. the preparation method of carbon fiber honeycomb as claimed in claim 2, is characterized in that: described former is moulding press, and described technological parameter is:
Molding temperature is 120 ~ 180 DEG C, and the time is 40 ~ 80min, and pressure is 0.5 ~ 0.7Mpa.
7. the preparation method of the carbon fiber honeycomb as described in claim 2 ~ 6 any one, is characterized in that: the cross section of described mould is continuous semi-hexagon shape shape.
8. the preparation method of carbon fiber honeycomb as claimed in claim 7, is characterized in that: described mould adopts aluminium alloy or mould steel to make.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201510150581.1A CN104842593B (en) | 2015-03-24 | 2015-03-24 | Carbon fiber honeycomb and preparation method thereof |
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|---|---|---|---|
| CN201510150581.1A CN104842593B (en) | 2015-03-24 | 2015-03-24 | Carbon fiber honeycomb and preparation method thereof |
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| CN104842593A true CN104842593A (en) | 2015-08-19 |
| CN104842593B CN104842593B (en) | 2018-01-12 |
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Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105694575A (en) * | 2016-04-13 | 2016-06-22 | 腰正钊 | Carbon fiber reinforced composite honeycomb-structured putty and preparation and construction methods thereof |
| CN105820571A (en) * | 2016-05-10 | 2016-08-03 | 河北科技大学 | Carbon fiber honeycomb reinforced polyimide foam material and preparation method thereof |
| CN105946246A (en) * | 2016-05-10 | 2016-09-21 | 河北科技大学 | Preparation method for carbon fiber honeycomb core materials |
| CN106427005A (en) * | 2016-09-28 | 2017-02-22 | 成都柒柒家祥科技有限公司 | Preparation technology for honeycomb supporting structure |
| CN106626438A (en) * | 2016-11-29 | 2017-05-10 | 北京卫星制造厂 | Carbon fiber honeycomb core supporting structure and preparation method thereof |
| CN107244087A (en) * | 2017-07-14 | 2017-10-13 | 苏州云逸航空复合材料结构有限公司 | The manufacture method of composite honeycomb and the equipment for manufacturing composite honeycomb |
| CN108112202A (en) * | 2017-12-15 | 2018-06-01 | 中国电子科技集团公司第十八研究所 | Power supply controller structure |
| CN108840697A (en) * | 2018-06-29 | 2018-11-20 | 航天材料及工艺研究所 | A kind of carbon/carbon compound material honeycomb and preparation method thereof |
| CN109249652A (en) * | 2018-08-22 | 2019-01-22 | 哈尔滨工程大学 | Full carbon fibre composite honeycomb and preparation method thereof |
| CN110039874A (en) * | 2018-11-22 | 2019-07-23 | 阜宁云逸航空复合材料有限公司 | A kind of production method of honeycomb |
| WO2019239002A1 (en) * | 2018-06-12 | 2019-12-19 | Sensapex Oy | Thermal expansion controlled micro- and nanopositioner and manufacturing method thereof |
| CN110599993A (en) * | 2019-09-24 | 2019-12-20 | 哈尔滨工程大学 | Carbon fiber sound baffle for underwater detection equipment |
| CN111016396A (en) * | 2019-12-13 | 2020-04-17 | 中国航空工业集团公司基础技术研究院 | Carbon fiber honeycomb core material node gluing method |
| CN114030241A (en) * | 2021-10-11 | 2022-02-11 | 航天材料及工艺研究所 | Carbon fiber composite material honeycomb, preparation method and application |
| CN114131954A (en) * | 2021-10-26 | 2022-03-04 | 中国船舶重工集团公司第七二五研究所 | Preparation method of grid structure reinforced foam sandwich composite material based on secondary forming |
| CN115352078A (en) * | 2022-08-26 | 2022-11-18 | 上海复合材料科技有限公司 | Composite material honeycomb and preparation method thereof |
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Cited By (22)
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| CN105694575A (en) * | 2016-04-13 | 2016-06-22 | 腰正钊 | Carbon fiber reinforced composite honeycomb-structured putty and preparation and construction methods thereof |
| CN105820571A (en) * | 2016-05-10 | 2016-08-03 | 河北科技大学 | Carbon fiber honeycomb reinforced polyimide foam material and preparation method thereof |
| CN105946246A (en) * | 2016-05-10 | 2016-09-21 | 河北科技大学 | Preparation method for carbon fiber honeycomb core materials |
| CN105820571B (en) * | 2016-05-10 | 2018-04-20 | 河北科技大学 | A kind of carbon fiber Honeycomb Polyimide foams and preparation method thereof |
| CN106427005A (en) * | 2016-09-28 | 2017-02-22 | 成都柒柒家祥科技有限公司 | Preparation technology for honeycomb supporting structure |
| CN106626438A (en) * | 2016-11-29 | 2017-05-10 | 北京卫星制造厂 | Carbon fiber honeycomb core supporting structure and preparation method thereof |
| CN107244087A (en) * | 2017-07-14 | 2017-10-13 | 苏州云逸航空复合材料结构有限公司 | The manufacture method of composite honeycomb and the equipment for manufacturing composite honeycomb |
| CN108112202A (en) * | 2017-12-15 | 2018-06-01 | 中国电子科技集团公司第十八研究所 | Power supply controller structure |
| WO2019239002A1 (en) * | 2018-06-12 | 2019-12-19 | Sensapex Oy | Thermal expansion controlled micro- and nanopositioner and manufacturing method thereof |
| CN108840697B (en) * | 2018-06-29 | 2021-07-13 | 航天材料及工艺研究所 | Carbon/carbon composite material honeycomb and preparation method thereof |
| CN108840697A (en) * | 2018-06-29 | 2018-11-20 | 航天材料及工艺研究所 | A kind of carbon/carbon compound material honeycomb and preparation method thereof |
| CN109249652A (en) * | 2018-08-22 | 2019-01-22 | 哈尔滨工程大学 | Full carbon fibre composite honeycomb and preparation method thereof |
| CN110039874A (en) * | 2018-11-22 | 2019-07-23 | 阜宁云逸航空复合材料有限公司 | A kind of production method of honeycomb |
| CN110599993A (en) * | 2019-09-24 | 2019-12-20 | 哈尔滨工程大学 | Carbon fiber sound baffle for underwater detection equipment |
| CN110599993B (en) * | 2019-09-24 | 2024-06-21 | 哈尔滨工程大学 | Carbon fiber sound baffle for underwater detection equipment |
| CN111016396A (en) * | 2019-12-13 | 2020-04-17 | 中国航空工业集团公司基础技术研究院 | Carbon fiber honeycomb core material node gluing method |
| CN114030241A (en) * | 2021-10-11 | 2022-02-11 | 航天材料及工艺研究所 | Carbon fiber composite material honeycomb, preparation method and application |
| CN114030241B (en) * | 2021-10-11 | 2024-05-14 | 航天材料及工艺研究所 | Carbon fiber composite honeycomb, preparation method and application |
| CN114131954A (en) * | 2021-10-26 | 2022-03-04 | 中国船舶重工集团公司第七二五研究所 | Preparation method of grid structure reinforced foam sandwich composite material based on secondary forming |
| CN114131954B (en) * | 2021-10-26 | 2024-06-28 | 中国船舶重工集团公司第七二五研究所 | Preparation method of grid structure reinforced foam sandwich composite material based on secondary molding |
| CN115352078A (en) * | 2022-08-26 | 2022-11-18 | 上海复合材料科技有限公司 | Composite material honeycomb and preparation method thereof |
| CN115352078B (en) * | 2022-08-26 | 2024-11-01 | 上海复合材料科技有限公司 | Composite honeycomb and preparation method thereof |
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| CN104842593B (en) | 2018-01-12 |
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