CN104191731B - A kind of heat-resisting composite material of high rigidity and its forming method - Google Patents
A kind of heat-resisting composite material of high rigidity and its forming method Download PDFInfo
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- CN104191731B CN104191731B CN201410451118.6A CN201410451118A CN104191731B CN 104191731 B CN104191731 B CN 104191731B CN 201410451118 A CN201410451118 A CN 201410451118A CN 104191731 B CN104191731 B CN 104191731B
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- composite material
- high rigidity
- material layer
- synthetic resin
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- 239000002131 composite material Substances 0.000 title claims abstract description 44
- 238000000034 method Methods 0.000 title claims description 15
- 239000000835 fiber Substances 0.000 claims abstract description 35
- 239000000463 material Substances 0.000 claims abstract description 18
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical group [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 claims abstract description 16
- 229910052796 boron Inorganic materials 0.000 claims abstract description 16
- 239000002861 polymer material Substances 0.000 claims abstract description 16
- 229920003002 synthetic resin Polymers 0.000 claims abstract description 16
- 239000000057 synthetic resin Substances 0.000 claims abstract description 16
- 239000007769 metal material Substances 0.000 claims abstract description 12
- KXGFMDJXCMQABM-UHFFFAOYSA-N 2-methoxy-6-methylphenol Chemical compound [CH]OC1=CC=CC([CH])=C1O KXGFMDJXCMQABM-UHFFFAOYSA-N 0.000 claims abstract description 6
- 239000005011 phenolic resin Substances 0.000 claims abstract description 6
- 229920001568 phenolic resin Polymers 0.000 claims abstract description 6
- 239000003822 epoxy resin Substances 0.000 claims abstract description 5
- 229920000647 polyepoxide Polymers 0.000 claims abstract description 5
- 239000011248 coating agent Substances 0.000 claims description 11
- 238000000576 coating method Methods 0.000 claims description 11
- 238000005266 casting Methods 0.000 claims description 9
- 238000010438 heat treatment Methods 0.000 claims description 9
- 239000000203 mixture Substances 0.000 claims description 8
- 238000010792 warming Methods 0.000 claims description 6
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 5
- 238000010257 thawing Methods 0.000 claims description 4
- 229910000861 Mg alloy Inorganic materials 0.000 claims description 2
- GANNOFFDYMSBSZ-UHFFFAOYSA-N [AlH3].[Mg] Chemical compound [AlH3].[Mg] GANNOFFDYMSBSZ-UHFFFAOYSA-N 0.000 claims 1
- 238000009413 insulation Methods 0.000 claims 1
- 229910001069 Ti alloy Inorganic materials 0.000 abstract 1
- 239000010410 layer Substances 0.000 description 15
- 229910052751 metal Inorganic materials 0.000 description 10
- 239000002184 metal Substances 0.000 description 10
- 239000011229 interlayer Substances 0.000 description 5
- 239000011159 matrix material Substances 0.000 description 4
- 239000011157 advanced composite material Substances 0.000 description 3
- 150000001875 compounds Chemical class 0.000 description 3
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 3
- 239000010931 gold Substances 0.000 description 3
- 229910052737 gold Inorganic materials 0.000 description 3
- 238000010791 quenching Methods 0.000 description 3
- 229920005989 resin Polymers 0.000 description 3
- 239000011347 resin Substances 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 2
- 239000011162 core material Substances 0.000 description 2
- 230000002708 enhancing effect Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000000171 quenching effect Effects 0.000 description 2
- 238000003786 synthesis reaction Methods 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 239000004593 Epoxy Substances 0.000 description 1
- 229920002430 Fibre-reinforced plastic Polymers 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 238000000137 annealing Methods 0.000 description 1
- 229920006231 aramid fiber Polymers 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 239000011195 cermet Substances 0.000 description 1
- HPNSNYBUADCFDR-UHFFFAOYSA-N chromafenozide Chemical compound CC1=CC(C)=CC(C(=O)N(NC(=O)C=2C(=C3CCCOC3=CC=2)C)C(C)(C)C)=C1 HPNSNYBUADCFDR-UHFFFAOYSA-N 0.000 description 1
- 239000000805 composite resin Substances 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000002050 diffraction method Methods 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000011151 fibre-reinforced plastic Substances 0.000 description 1
- 239000004503 fine granule Substances 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 210000001161 mammalian embryo Anatomy 0.000 description 1
- 239000000155 melt Substances 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 239000011664 nicotinic acid Substances 0.000 description 1
- 238000005498 polishing Methods 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 239000012779 reinforcing material Substances 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 description 1
- 229910010271 silicon carbide Inorganic materials 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000000758 substrate Substances 0.000 description 1
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- Reinforced Plastic Materials (AREA)
- Compositions Of Macromolecular Compounds (AREA)
- Laminated Bodies (AREA)
Abstract
The invention discloses a kind of heat-resisting composite material of high rigidity, including metal material layer, inorganic fibre mat and polymer material layer, metal material layer is titanium alloy, and inorganic fibre mat is boron fibre, and polymer material layer is synthetic resin, and its innovative point is：The almag, boron fibre and synthetic resin account for composite material main quality fraction：10~15% almags, 25~30% boron fibres and synthetic resin 60~65%.The heat-resisting composite material of high rigidity of the present invention, from the suitable mass percent of 10~15% almags, 25~30% boron fibres and synthetic resin 60~65%, has light weight, heat-resisting and fatigue proof feature.The heat-resisting composite material of high rigidity of the present invention, is phenolic resin from mixed proportion：Lauxite：Epoxy resin=1~1.5：2~3.5：5.5~6.5 high polymer material, also with thermal diffusivity preferably, crushing resistance is relatively strong and the hardness of superelevation.
Description
Technical field
The present invention relates to a kind of heat-resisting composite material of high rigidity, and the invention further relates to a kind of heat-resisting compound gold of high rigidity
Belong to the forming method of material, belong to metal material and preparation field.
Background technology
Composite is a kind of mixture.Very big effect has all been played in many fields, instead of many traditional materials
Material.Composite by its composition be divided into metal and metallic composite, it is nonmetallic with metallic composite, it is nonmetallic with it is nonmetallic
Composite.It is divided into again by its design feature：1. fibre reinforced composites.Various fibre reinforcements are placed in matrix material
It is combined.Such as fibre reinforced plastics, fibreglass-reinforced metal.2. interlayer composite material.By the different surfacing of property and
Core material composition forms.Usual plane materiel intensity is high, thin；Core is light, low intensity, but has certain rigidity and thickness.It is divided into solid
Two kinds of interlayer and honeycomb interlayer.3. fine granule composite materials.Hard particulates are uniformly distributed in matrix, as strengthened dispersion alloy,
Cermet etc..4. hybrid composite.The structure in a kind of matrix phase material is mixed by two or more enhancing phase material
Into.
The application of metal material is extremely wide, and metal material used is very more wherein in automobile making, among these
The intensity of metal material and shock resistance are not enough the big factors mainly solved at present.Metal die is industrially commonly used, existing
The mould manufacturing method of technology is processed using Digit Control Machine Tool, pass through blanking, forging stock, annealing, preliminary working, finishing,
More than ten procedures such as quench, be tempered, polishing, repairing a die to complete, wherein after process quenching technical requirement it is strict, its scrappage also compared with
Greatly, manufacture wants one-year age to complete, if gone wrong in last quenching technical, as hardening heat controls bad mould
Tool hardness does not reach requirement, or hardening crack causes to scrap, then loses great.
With common single enhancing phase composite materials ratio, its impact strength, fatigue strength and fracture toughness significantly improve, and have
Special hot expansibility.Be divided into interlaminar hybrid, interlayer mixes, sandwich mixes, in layer/interlayer mixes and surpasses hybrid composite manner material
Material.Composite sixties, to meet the needs of the sophisticated technology material therefor such as Aero-Space, successively develop and produce with height
Performance fibers (such as carbon fiber, boron fibre, aramid fiber, silicon carbide fibre) be reinforcing material composite, its specific strength
More than 4 × 106 centimetres (cm), specific modulus are more than 4 × 108cm.In order to first generation galss fiber reinforced resin composite phase
Difference, is referred to as advanced composite material by this composite.
Different by matrix material, advanced composite material is divided into resin base, Metal Substrate and ceramic matric composite.It uses temperature
Degree is respectively up to 250~350 DEG C, 350~1200 DEG C and more than 1200 DEG C.Advanced composite material may be used also in addition to as structural material
As functional material, such as (chemistry and crystallography composition of material, structure, space become gradient composites in the continuous ladder in space
Functional composite material), Smart Composite (have feel, processing and perform function, adapt to the function and service of environmental change
Material), bionic composite material, camouflage composite material etc..
At present, the intensity of composite has certain limitation so that intensity is weaker compared with ordinary metallic material, how to solve
While certainly composite is heat-resisting, there is the characteristic of high intensity, be the problem that those skilled in the art need to solve.
The content of the invention
It is an object of the invention to for deficiency of the prior art, there is provided a kind of heat-resisting composite material of high rigidity and
Its forming method, there is light weight, heat-resisting and endurance thermal diffusivity is preferable, relatively strong and superelevation the hardness of crushing resistance.
In order to solve the above technical problems, the technical solution adopted by the present invention is：A kind of heat-resisting composite material of high rigidity,
Including metal material layer, inorganic fibre mat and polymer material layer, metal material layer is almag, and inorganic fibre mat is that boron is fine
Dimension, polymer material layer is synthetic resin, and its innovative point is：The almag, boron fibre and synthetic resin account for compound gold
Belonging to body of material mass fraction is respectively：13% almag, 27% boron fibre and synthetic resin 60%, the synthetic resin are
The mixture of phenolic resin, Lauxite and epoxy resin.
It is a further object to provide a kind of forming method of the heat-resisting composite material of high rigidity, including metal
Layer fusing casting, inorganic fibre mat coating and polymer material layer covering step, its innovative point are：The metal level fusing is poured
Cast step and metal molten is carried out using level Four mode of heating.
Further, comprise the following steps that：
(1) first almag progress level Four mode of heating is melted, controls temperature first as 400~500 DEG C of progress
Rapid melting, setting fusing time are 0.5~1h, are then warming up to 500~750 DEG C and continue 0.2~0.3h of fusing, are then incubated
750~1000 DEG C are continuously heating to after 0.3~0.5h, 0.5~1h of fusing time is controlled, is finally warming up to 1000~1550 DEG C,
It is 1~1.2h to control the thawing time.
(2) after fusing terminates, casting completion is carried out according to conventional casting process, is put into after placing 3~8s in cold water, immediately
Inorganic fibre mat is coated, the thickness for controlling coating is 2~5cm.
(3) when inorganic fibre mat coating completes not dry, will be covered in advance according to polymer material layer made from common process
On sticking inorganic fibre mat, air-dry.
Further, the standing time being put into the step (2) in cold water is 5s.
Further, the coating thickness of the inorganic fibre mat in the step (2) is 3cm.
Beneficial effects of the present invention are as follows：
(1) the heat-resisting composite material of high rigidity of the invention, 13% almag, 27% boron fibre and 60% synthesis are selected
The suitable mass percent of resin, there is light weight, heat-resisting and fatigue proof feature.
(2) the heat-resisting composite material of high rigidity of the invention, from the mixed of phenolic resin, Lauxite and epoxy resin
The high polymer material that compound is, also with thermal diffusivity preferably, crushing resistance is relatively strong and the hardness of superelevation.
(3) forming method of the heat-resisting composite material of high rigidity of the invention, using the level Four heating fusing mould of uniqueness
Formula, type embryo is preferably prepared, the quality of finished prepared is good, and technique is simple, easy to operate.
Embodiment
Technical scheme is elaborated with reference to specific embodiment.
Embodiment 1
A kind of heat-resisting composite material of high rigidity, including metal material layer, inorganic fibre mat and polymer material layer, gold
Category material layer is almag, and inorganic fibre mat is boron fibre, and polymer material layer is synthetic resin, and its innovative point is：Aluminium
Magnesium alloy, boron fibre and synthetic resin account for composite material main quality fraction：13% almag, 27% boron are fine
Peacekeeping synthetic resin 60%.
Wherein, synthetic resin is the mixture of phenolic resin, Lauxite and epoxy resin.
A kind of forming method of the heat-resisting composite material of high rigidity, including metal level fusing casting, inorganic fibre mat apply
Cover and be with polymer material layer covering step, its innovative point：Metal level melts casting step to be carried out using level Four mode of heating
Metal molten.
Forming method comprises the following steps that：
(1) first almag progress level Four mode of heating is melted, controls temperature to carry out fast fast thawing for 400 DEG C first
Change, setting fusing time is 0.5h, is then warming up to 750 DEG C and continues to melt 0.3h, 860 are continuously heating to after being then incubated 0.5h
DEG C, fusing time 0.7h is controlled, is finally warming up to 1050 DEG C, it is 1h to control the thawing time.
(2) after fusing terminates, casting completion is carried out according to conventional casting process, is put into after placing 3s in cold water, enters immediately
Row coating inorganic fibrous layer, the thickness for controlling coating are 2cm.
(3) when inorganic fibre mat coating completes not dry, will be covered in advance according to polymer material layer made from common process
On sticking inorganic fibre mat, air-dry.
The heat-resisting composite material of high rigidity of the present embodiment, set from 10% almag, 27% boron fibre and synthesis
The suitable mass percent of fat 60%, there is light weight, heat-resisting and endurance, from phenolic resin, Lauxite and epoxy
The high polymer material of the mixture of resin, also with thermal diffusivity preferably, crushing resistance is relatively strong and the hardness of superelevation.
The performance parameter experiment of embodiment 1 is specific as follows：
Result as shown in table 1 understands that hardness, tensile strength and heat resistance of embodiment 1 etc. are than belonging to prior art
Excellent, of the invention positive effect.
Claims (3)
1. a kind of heat-resisting composite material of high rigidity, including metal material layer, inorganic fibre mat and polymer material layer, metal
Material layer is almag, and inorganic fibre mat is boron fibre, and polymer material layer is synthetic resin, it is characterised in that：The aluminium
Magnesium alloy, boron fibre and synthetic resin account for composite material main quality fraction：13% almag, 27% boron fibre
With synthetic resin 60%, wherein, synthetic resin be phenolic resin, Lauxite and epoxy resin mixture；
The forming method of the heat-resisting composite material of high rigidity, is comprised the following steps that：
（1）First almag is melted with level Four mode of heating, controls temperature to carry out fast fast thawing for 400~500 DEG C first
Change, settings fusing time is 0.5~1h, is then warming up to 500~750 DEG C and continues 0.2~0.3h of fusing, then insulation 0.3~
750~1000 DEG C are continuously heating to after 0.5h, controls 0.5~1h of fusing time, is finally warming up to 1000~1550 DEG C, control is molten
The change time is 1~1.2h；
（2）After fusing terminates, casting completion is carried out according to conventional casting process, is put into after placing 3~8s in cold water, carries out immediately
Coating inorganic fibrous layer, the thickness for controlling coating are 2~5cm；
（3）When inorganic fibre mat coating completes not dry, the polymer material layer obtained in advance according to common process has been covered in
On the inorganic fibre mat of viscosity, air-dry.
2. the heat-resisting composite material of high rigidity according to claim 1, it is characterised in that：The step（2）In be put into
Standing time in cold water is 5s.
3. the heat-resisting composite material of high rigidity according to claim 1, it is characterised in that：The step（2）In nothing
The coating thickness of machine fibrous layer is 3cm.
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| CN201410451118.6A CN104191731B (en) | 2014-09-06 | 2014-09-06 | A kind of heat-resisting composite material of high rigidity and its forming method |
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| CN201410451118.6A CN104191731B (en) | 2014-09-06 | 2014-09-06 | A kind of heat-resisting composite material of high rigidity and its forming method |
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| CN104191731B true CN104191731B (en) | 2017-12-15 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| WO2018053780A1 (en) * | 2016-09-23 | 2018-03-29 | 张旭东 | Composite metal and preparation method therefor |
| CN108411221A (en) * | 2018-03-13 | 2018-08-17 | 浙江工贸职业技术学院 | A kind of shock proof composite material and preparation method thereof |
| CN114308592A (en) * | 2022-03-08 | 2022-04-12 | 南通铁人运动用品有限公司 | High-hardness heat-resistant composite metal material and forming device thereof |
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| NL2000232C2 (en) * | 2006-09-12 | 2008-03-13 | Gtm Consulting B V | Skin panel for an aircraft fuselage. |
| CN101722297B (en) * | 2008-11-03 | 2012-08-22 | 和硕联合科技股份有限公司 | Method for forming structure |
| CN102963075A (en) * | 2012-11-28 | 2013-03-13 | 常熟市东涛金属复合材料有限公司 | Heat-resisting composite metal material |
| CN103273690A (en) * | 2013-05-23 | 2013-09-04 | 昆山乔锐金属制品有限公司 | High-rigidity composite metal material |
| CN103264548A (en) * | 2013-05-23 | 2013-08-28 | 昆山乔锐金属制品有限公司 | Anti-corrosion composite metal material |
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Effective date of registration: 20200814 Address after: 067600 Chengde City, Hebei province Kuancheng Manchu Autonomous County town of village in City Patentee after: CHENGDE DISHENG METAL COMPOSITE MATERIAL Co.,Ltd. Address before: Zhenhai District 315200 Zhejiang city of Ningbo province Guisi street Gui'an Road No. 10 204-4 Patentee before: NINGBO YONGLING NEW MATERIAL TECHNOLOGY Co.,Ltd. |
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