CN114411070A - Fiber-reinforced metal-based composite material and preparation method thereof - Google Patents
Fiber-reinforced metal-based composite material and preparation method thereof Download PDFInfo
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- 238000002360 preparation method Methods 0.000 title claims abstract description 45
- 229910052751 metal Inorganic materials 0.000 title claims abstract description 41
- 239000002184 metal Substances 0.000 title claims abstract description 41
- 239000002131 composite material Substances 0.000 title claims abstract description 34
- 239000000919 ceramic Substances 0.000 claims abstract description 55
- 239000011156 metal matrix composite Substances 0.000 claims abstract description 44
- 238000007731 hot pressing Methods 0.000 claims abstract description 42
- 239000011888 foil Substances 0.000 claims abstract description 36
- 239000000463 material Substances 0.000 claims abstract description 35
- 239000000835 fiber Substances 0.000 claims abstract description 33
- 239000000853 adhesive Substances 0.000 claims abstract description 8
- 230000001070 adhesive effect Effects 0.000 claims abstract description 8
- 239000012528 membrane Substances 0.000 claims abstract description 7
- 238000000034 method Methods 0.000 claims description 25
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 18
- 238000010041 electrostatic spinning Methods 0.000 claims description 13
- 229910052757 nitrogen Inorganic materials 0.000 claims description 9
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 8
- CPLXHLVBOLITMK-UHFFFAOYSA-N Magnesium oxide Chemical compound [Mg]=O CPLXHLVBOLITMK-UHFFFAOYSA-N 0.000 claims description 6
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 6
- WYURNTSHIVDZCO-UHFFFAOYSA-N Tetrahydrofuran Chemical compound C1CCOC1 WYURNTSHIVDZCO-UHFFFAOYSA-N 0.000 claims description 6
- MCMNRKCIXSYSNV-UHFFFAOYSA-N Zirconium dioxide Chemical compound O=[Zr]=O MCMNRKCIXSYSNV-UHFFFAOYSA-N 0.000 claims description 6
- 229910052786 argon Inorganic materials 0.000 claims description 4
- RSWGJHLUYNHPMX-UHFFFAOYSA-N Abietic-Saeure Natural products C12CCC(C(C)C)=CC2=CCC2C1(C)CCCC2(C)C(O)=O RSWGJHLUYNHPMX-UHFFFAOYSA-N 0.000 claims description 3
- PNEYBMLMFCGWSK-UHFFFAOYSA-N Alumina Chemical compound [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 claims description 3
- 229920001651 Cyanoacrylate Polymers 0.000 claims description 3
- 239000004375 Dextrin Substances 0.000 claims description 3
- 229920001353 Dextrin Polymers 0.000 claims description 3
- MWCLLHOVUTZFKS-UHFFFAOYSA-N Methyl cyanoacrylate Chemical compound COC(=O)C(=C)C#N MWCLLHOVUTZFKS-UHFFFAOYSA-N 0.000 claims description 3
- KHPCPRHQVVSZAH-HUOMCSJISA-N Rosin Natural products O(C/C=C/c1ccccc1)[C@H]1[C@H](O)[C@@H](O)[C@@H](O)[C@@H](CO)O1 KHPCPRHQVVSZAH-HUOMCSJISA-N 0.000 claims description 3
- 229920002472 Starch Polymers 0.000 claims description 3
- RKFMOTBTFHXWCM-UHFFFAOYSA-M [AlH2]O Chemical compound [AlH2]O RKFMOTBTFHXWCM-UHFFFAOYSA-M 0.000 claims description 3
- 229910002113 barium titanate Inorganic materials 0.000 claims description 3
- JRPBQTZRNDNNOP-UHFFFAOYSA-N barium titanate Chemical compound [Ba+2].[Ba+2].[O-][Ti]([O-])([O-])[O-] JRPBQTZRNDNNOP-UHFFFAOYSA-N 0.000 claims description 3
- 239000011230 binding agent Substances 0.000 claims description 3
- 235000019425 dextrin Nutrition 0.000 claims description 3
- 239000007849 furan resin Substances 0.000 claims description 3
- 239000001307 helium Substances 0.000 claims description 3
- 229910052734 helium Inorganic materials 0.000 claims description 3
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 claims description 3
- 239000001866 hydroxypropyl methyl cellulose Substances 0.000 claims description 3
- 229920003088 hydroxypropyl methyl cellulose Polymers 0.000 claims description 3
- 235000010979 hydroxypropyl methyl cellulose Nutrition 0.000 claims description 3
- UFVKGYZPFZQRLF-UHFFFAOYSA-N hydroxypropyl methyl cellulose Chemical compound OC1C(O)C(OC)OC(CO)C1OC1C(O)C(O)C(OC2C(C(O)C(OC3C(C(O)C(O)C(CO)O3)O)C(CO)O2)O)C(CO)O1 UFVKGYZPFZQRLF-UHFFFAOYSA-N 0.000 claims description 3
- 239000011261 inert gas Substances 0.000 claims description 3
- 239000000395 magnesium oxide Substances 0.000 claims description 3
- 229910052754 neon Inorganic materials 0.000 claims description 3
- GKAOGPIIYCISHV-UHFFFAOYSA-N neon atom Chemical compound [Ne] GKAOGPIIYCISHV-UHFFFAOYSA-N 0.000 claims description 3
- 125000000914 phenoxymethylpenicillanyl group Chemical group CC1(S[C@H]2N([C@H]1C(=O)*)C([C@H]2NC(COC2=CC=CC=C2)=O)=O)C 0.000 claims description 3
- 235000019353 potassium silicate Nutrition 0.000 claims description 3
- RMAQACBXLXPBSY-UHFFFAOYSA-N silicic acid Chemical compound O[Si](O)(O)O RMAQACBXLXPBSY-UHFFFAOYSA-N 0.000 claims description 3
- 239000000377 silicon dioxide Substances 0.000 claims description 3
- NTHWMYGWWRZVTN-UHFFFAOYSA-N sodium silicate Chemical compound [Na+].[Na+].[O-][Si]([O-])=O NTHWMYGWWRZVTN-UHFFFAOYSA-N 0.000 claims description 3
- 239000008107 starch Substances 0.000 claims description 3
- 235000019698 starch Nutrition 0.000 claims description 3
- YLQBMQCUIZJEEH-UHFFFAOYSA-N tetrahydrofuran Natural products C=1C=COC=1 YLQBMQCUIZJEEH-UHFFFAOYSA-N 0.000 claims description 3
- KHPCPRHQVVSZAH-UHFFFAOYSA-N trans-cinnamyl beta-D-glucopyranoside Natural products OC1C(O)C(O)C(CO)OC1OCC=CC1=CC=CC=C1 KHPCPRHQVVSZAH-UHFFFAOYSA-N 0.000 claims description 3
- 235000015112 vegetable and seed oil Nutrition 0.000 claims description 3
- 239000008158 vegetable oil Substances 0.000 claims description 3
- 229910052724 xenon Inorganic materials 0.000 claims description 3
- FHNFHKCVQCLJFQ-UHFFFAOYSA-N xenon atom Chemical compound [Xe] FHNFHKCVQCLJFQ-UHFFFAOYSA-N 0.000 claims description 3
- 239000002905 metal composite material Substances 0.000 abstract description 3
- 239000000523 sample Substances 0.000 description 30
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Chemical compound O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 13
- 239000002245 particle Substances 0.000 description 11
- 238000002791 soaking Methods 0.000 description 9
- 238000005406 washing Methods 0.000 description 9
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 description 8
- 229910052782 aluminium Inorganic materials 0.000 description 8
- 238000004140 cleaning Methods 0.000 description 8
- 239000008367 deionised water Substances 0.000 description 8
- 229910021641 deionized water Inorganic materials 0.000 description 8
- 230000007935 neutral effect Effects 0.000 description 8
- 229910000838 Al alloy Inorganic materials 0.000 description 6
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 4
- -1 aluminum carboxylate Chemical class 0.000 description 4
- 239000011248 coating agent Substances 0.000 description 4
- 238000000576 coating method Methods 0.000 description 4
- 230000003014 reinforcing effect Effects 0.000 description 4
- 241000282414 Homo sapiens Species 0.000 description 2
- 239000013068 control sample Substances 0.000 description 2
- 238000000151 deposition Methods 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 239000007791 liquid phase Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000000843 powder Substances 0.000 description 2
- 238000009715 pressure infiltration Methods 0.000 description 2
- 239000002002 slurry Substances 0.000 description 2
- 238000003756 stirring Methods 0.000 description 2
- 239000002699 waste material Substances 0.000 description 2
- QGZKDVFQNNGYKY-UHFFFAOYSA-N Ammonia Chemical compound N QGZKDVFQNNGYKY-UHFFFAOYSA-N 0.000 description 1
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 229910020491 K2TiF6 Inorganic materials 0.000 description 1
- 239000000654 additive Substances 0.000 description 1
- 230000000996 additive effect Effects 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000008021 deposition Effects 0.000 description 1
- 239000012153 distilled water Substances 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000003822 epoxy resin Substances 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 229910002804 graphite Inorganic materials 0.000 description 1
- 239000010439 graphite Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000011065 in-situ storage Methods 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000704 physical effect Effects 0.000 description 1
- 229920000647 polyepoxide Polymers 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 238000007670 refining Methods 0.000 description 1
- 239000011208 reinforced composite material Substances 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- OXYOBDANCFSCGB-UHFFFAOYSA-J silicon(4+) tetraformate Chemical compound [Si+4].[O-]C=O.[O-]C=O.[O-]C=O.[O-]C=O OXYOBDANCFSCGB-UHFFFAOYSA-J 0.000 description 1
- 238000010532 solid phase synthesis reaction Methods 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
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Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C47/00—Making alloys containing metallic or non-metallic fibres or filaments
- C22C47/02—Pretreatment of the fibres or filaments
- C22C47/06—Pretreatment of the fibres or filaments by forming the fibres or filaments into a preformed structure, e.g. using a temporary binder to form a mat-like element
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C47/00—Making alloys containing metallic or non-metallic fibres or filaments
- C22C47/20—Making alloys containing metallic or non-metallic fibres or filaments by subjecting to pressure and heat an assembly comprising at least one metal layer or sheet and one layer of fibres or filaments
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C49/00—Alloys containing metallic or non-metallic fibres or filaments
- C22C49/14—Alloys containing metallic or non-metallic fibres or filaments characterised by the fibres or filaments
Abstract
The invention relates to the technical field of composite material preparation, in particular to a fiber reinforced metal matrix composite material and a preparation method thereof; the preparation method comprises the following preparation steps: alternately adhering ceramic membranes and metal foils into a whole through an adhesive to obtain a prefabricated composite material, wherein the metal foils are N layers, the ceramic membranes are N-1 layers, and N is more than or equal to 2; placing the prefabricated composite material into a mold, and carrying out hot pressing in a hot pressing furnace to obtain a fiber reinforced metal matrix composite material; the design of the preparation method of the fiber reinforced metal matrix composite material is used for solving the technical problems of low thermal expansion coefficient, complex preparation process, fussy preparation process and high cost of the existing metal composite material in the prior art.
Description
Technical Field
The invention relates to the technical field of composite material preparation, in particular to a fiber reinforced metal matrix composite material and a preparation method thereof.
Background
With the rising of national economic strength in recent years, many large-scale enterprises pay more and more attention to the problems of resource waste and high material cost, and according to incomplete statistics, the resource waste caused by material fatigue damage and corrosion damage accounts for 50% in this year. For this reason, the development of new materials is strongly promoted in the country in recent years, and the new materials are one of four high and new technologies which are well known to guide the future development of the whole world for human beings. The composite material has a crucial position as one of new materials, and with the rapid development of the fields of transportation, aerospace and the like, the requirements on the material performance are more and more strict, for example, high temperature resistance, high heat conduction coefficient, tensile strength, wear resistance and the like are required while high light and high temperature are required. As for the development prospect at present, the alloy material with single performance can not meet the requirement of human on high-tech development, and the birth of the composite material opens up a new era of the material world.
At present, the composite material is applied to aerospace in many cases, and particularly, parts on an airplane body need to have all-round excellent performance, and the existing airplane body material has certain defects and needs to further improve the performance of the material. The flexible ceramic membrane reinforced metal matrix composite material has a completely exposed head angle and becomes a main composite material required by the fuselage. At present, the materials used for the fuselage must have good properties, and the preparation cost thereof must be reduced, so that the developed composite materials are meaningful. The preparation process of the metal composite material mainly comprises a solid phase method, a liquid phase method and an in-situ generation method. In the past, liquid phase methods have been used for many studies, for example: the processes of vacuum pressure infiltration, non-pressure infiltration and the like exist, but the processes have the problems of complex operation, high equipment cost, complex preparation process and the like.
Patent CN 202010436749.6 discloses that the reinforcing particles comprise SiC particles, CaZr2(PO4)3Particles and ZrV2O7The particles are uniformly mixed according to a certain proportion and wrapped in the aluminum alloy thin strip, then the sealing position of the aluminum alloy thin strip is welded to prepare an aluminum wire filled with the reinforcing particles, and the aluminum wire is heated and melted in an induction heater with the temperature of 800-1000 ℃. And atomizing the molten droplets into micro-nano aluminum alloy droplets and reinforcing particles by using high-pressure nitrogen, and depositing together to form the aluminum-based composite material with the low thermal expansion coefficient, wherein the pressure of the high-pressure nitrogen is 2-5 MPa, the temperature is-10 ℃ to-20 ℃, the deposition distance is 200-300 mm, the method has high operation requirement, needs professional technicians to operate, and only can prepare the particle reinforced composite material.
Patent CN 201310042089.3 discloses soaking SiC particles for 72h, stirring for 30min every 5h, repeatedly washing with distilled water until pH is about 7, finally preparing SiC slurry, taking 20h when preparing reinforcement particles, then preparing aluminum alloy solution under the protection of argon gas of 159ml/min, mixing to slurry, heating and stirring with stainless steel stirrer and graphite stirrer, then placing into extrusion die with temperature of 400 ℃ after fully fusing, simultaneously applying pressure of 100MPa and keeping for 10min, cooling, taking out from die, and preparing aluminum matrix composite. The method has the disadvantages of complicated preparation process, overlong preparation period, difficulty in quantitative production, high cost, strict preparation conditions, high pressure and operation of professional operators, and the method has limitation in use range and can only use the particle reinforced metal matrix composite.
Patent CN201210478762.3 discloses to K2TiF6Adding powder serving as a powder additive into an aluminum alloy solution at a high temperature, introducing reducing gas for protection (ammonia gas is used in the patent), treating a reaction system by using a low-frequency rotating magnetic field at the periphery of a crucible, and finally refining and pouring the metal solution into a mold to obtain a composite material; the preparation process has high professional requirements, needs professional operation, has high current, has high requirements on equipment, has low volume fraction of reinforcing items, is mostly oxide, and can only prepare particles or whiskers (short fibers)Dimension) is enhanced.
Therefore, in view of the above problems, the present invention is urgently needed to provide a fiber reinforced metal matrix composite material and a preparation method thereof.
Disclosure of Invention
The invention aims to provide a fiber reinforced metal matrix composite and a preparation method thereof, and the fiber reinforced metal matrix composite is designed to solve the technical problems of low thermal expansion coefficient, complex preparation process and high cost of the existing metal composite in the prior art.
The invention provides a preparation method of a fiber reinforced metal matrix composite, which comprises the following preparation steps:
alternately adhering ceramic membranes and metal foils into a whole through an adhesive to obtain a prefabricated composite material, wherein the metal foils are N layers, the ceramic membranes are N-1 layers, and N is more than or equal to 2;
and putting the prefabricated composite material into a mould, and carrying out hot pressing in a hot pressing furnace to obtain the fiber reinforced metal matrix composite material.
Preferably, the thickness of the pre-fabricated composite material is from 0.42mm to 10 mm.
Preferably, electrostatic spinning with the thickness of 0.02mm-0.1mm is adopted to prepare a ceramic film; the thickness of the metal foil is 0.02mm-0.1 mm.
Preferably, in the hot pressing process, the hot pressing is performed under an inert atmosphere.
Preferably, the material of the ceramic film includes at least one of an alumina ceramic film, a zirconia ceramic film, a barium titanate ceramic film, a silica ceramic film, or a magnesia ceramic film.
Preferably, the binder comprises at least one of hydroxypropyl methylcellulose, silica sol, PVA solution, starch, hydroxy aluminum sol, tetrahydrofuran, cyanoacrylate, vegetable oil, rosin, dextrin, water glass, furan resin.
Preferably, a hot-pressing furnace is adopted for hot pressing, and the process parameters of the hot-pressing furnace are that the hot-pressing temperature is 100-.
Preferably, the inert gas is one or more of nitrogen, argon, helium, neon and xenon.
Preferably, in the preparation process of the ceramic film, the ceramic film is prepared by adopting an electrostatic spinning process, and the electrostatic spinning parameters are as follows: the collection distance is 10-15cm, the voltage is 10-18kv, the solution feeding speed is 1.8-2ml/h, and the rotation speed of the roller collector is 1800 and 2000 rpm.
The invention also provides a fiber reinforced metal matrix composite material obtained based on the preparation method of the fiber reinforced metal matrix composite material.
Compared with the prior art, the fiber reinforced metal matrix composite and the preparation method thereof provided by the invention have the following advantages:
1. the fiber-reinforced metal-based composite material prepared by the preparation method of the fiber-reinforced metal-based composite material provided by the invention has high temperature resistance and high heat conduction coefficient, and meets the application in the field of aviation.
2. The preparation method of the fiber reinforced metal matrix composite material provided by the invention has the advantages of simple preparation process, simple equipment, low energy consumption and reduced manufacturing cost.
3. The preparation method of the fiber reinforced metal matrix composite material provided by the invention has no pollution in the preparation process and meets the requirement of environmental protection.
Detailed Description
The technical solutions of the present invention will be described clearly and completely below, and it should be apparent that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention provides a preparation method of a fiber reinforced metal matrix composite, which comprises the following preparation steps:
s1) alternately adhering the ceramic films and the metal foils into a whole through an adhesive to obtain a prefabricated composite material, wherein the metal foils are N layers, the ceramic films are N-1 layers, and N is more than or equal to 2;
s2) putting the prefabricated composite material into a mould, and carrying out hot pressing in a hot pressing furnace to obtain the fiber reinforced metal matrix composite material.
Specifically, the thickness of the prefabricated composite material is 0.42mm-10 mm.
Specifically, electrostatic spinning with the thickness of 0.02mm-0.1mm is adopted to prepare a ceramic film; the thickness of the metal foil is 0.02mm-0.1 mm.
Specifically, in the hot pressing process, hot pressing is performed under an inert atmosphere.
Specifically, the material of the ceramic film includes at least one of an alumina ceramic film, a zirconia ceramic film, a barium titanate ceramic film, a silica ceramic film, or a magnesia ceramic film.
Specifically, the binder includes at least one of hydroxypropyl methylcellulose, silica sol, PVA solution, starch, hydroxy aluminum sol, tetrahydrofuran, cyanoacrylate, vegetable oil, rosin, dextrin, water glass, and furan resin.
Specifically, a hot-pressing furnace is adopted for hot pressing, and the process parameters of the hot-pressing furnace are that the hot-pressing temperature is 100-.
Specifically, the inert gas is one or more of nitrogen, argon, helium, neon and xenon.
Specifically, in the preparation process of the ceramic film, an electrostatic spinning process is adopted for preparation, and electrostatic spinning parameters are as follows: the collection distance is 10-15cm, the voltage is 10-18kv, the solution feeding speed is 1.8-2ml/h, and the rotation speed of the roller collector is 1800 and 2000 rpm.
The invention also provides a fiber reinforced metal matrix composite material obtained based on the preparation method of the fiber reinforced metal matrix composite material.
Example one
A fiber reinforced metal matrix composite (sample 1) was prepared comprising the following preparation steps:
101) selecting concentrated aluminum carboxylate sol, and setting electrostatic spinning parameters as follows: collecting the solution with the collection distance of 12cm, the voltage of 12kv, the solution feeding speed of 1.8ml/h and the rotating speed of 1800rpm of a roller collector to prepare and obtain a ceramic film with the thickness of 20 microns; selecting 20 μm metal foil;
102) cleaning the metal foil by ultrasonic waves, repeatedly washing the metal foil by deionized water after cleaning until the water is neutral, and airing for 2 hours for later use; soaking the ceramic film in absolute alcohol for 30min, repeatedly washing the ceramic film with deionized water to be neutral after soaking, and airing for 1h for later use;
103) coating PVA solution with the mass fraction of 3% on the upper surface and the lower surface of each ceramic film and each metal foil, and sequentially and alternately stacking the ceramic films and the metal foils into a whole to obtain a prefabricated composite material, wherein 11 layers of metal foils and 10 layers of ceramic films are stacked into a whole in an ABAB stacking manner;
104) and (3) putting the prefabricated composite material into a hot pressing furnace filled with nitrogen, and carrying out hot pressing to obtain the fiber reinforced metal matrix composite material (sample 1), wherein the hot pressing temperature is 600 ℃, the hot pressing pressure is 10MPa, and the pressure maintaining time is 30 min.
The properties of sample 1 are shown in Table 1.
The control sample was an aluminum alloy thin strip purchased from Yinuo Metal materials, Inc. of Dongguan.
Example two
A fiber reinforced metal matrix composite (sample 2) was prepared comprising the following preparation steps:
201) selecting concentrated aluminum carboxylate sol, and setting electrostatic spinning parameters as follows: collecting the solution with the collection distance of 12cm, the voltage of 12kv, the solution feeding speed of 1.8ml/h and the rotating speed of 1800rpm of a roller collector to prepare and obtain a ceramic film with the thickness of 20 microns; selecting 20 μm metal foil;
202) cleaning the metal foil by ultrasonic waves, repeatedly washing the metal foil by deionized water after cleaning until the water is neutral, and airing for 2 hours for later use; soaking the ceramic film in absolute alcohol for 30min, repeatedly washing the ceramic film with deionized water to be neutral after soaking, and airing for 1h for later use;
203) coating PVA solution with the mass fraction of 3% on the upper surface and the lower surface of each ceramic film and each metal foil, and sequentially and alternately stacking the ceramic films and the metal foils into a whole to obtain a prefabricated composite material, wherein 15 layers of metal foils and 14 layers of ceramic films are stacked into a whole according to an ABAB stacking mode;
204) and (3) putting the prefabricated composite material into a hot pressing furnace filled with nitrogen, and carrying out hot pressing to obtain the fiber reinforced metal matrix composite material (sample 2), wherein the hot pressing temperature is 600 ℃, the hot pressing pressure is 10MPa, and the pressure maintaining time is 30 min.
The properties of sample 2 are shown in Table 1.
EXAMPLE III
A fiber reinforced metal matrix composite (sample 3) was prepared comprising the following preparation steps:
301) selecting concentrated aluminum carboxylate sol, and setting electrostatic spinning parameters as follows: collecting the solution with the collection distance of 12cm, the voltage of 12kv, the solution feeding speed of 1.8ml/h and the rotating speed of 1800rpm of a roller collector to prepare and obtain a ceramic film with the thickness of 20 microns; selecting 20 μm metal foil;
302) cleaning the metal foil by ultrasonic waves, repeatedly washing the metal foil by deionized water after cleaning until the water is neutral, and airing for 2 hours for later use; soaking the ceramic film in absolute alcohol for 30min, repeatedly washing the ceramic film with deionized water to be neutral after soaking, and airing for 1h for later use;
303) coating PVA solution with the mass fraction of 3% on the upper surface and the lower surface of each ceramic film and each metal foil, and sequentially and alternately stacking the ceramic films and the metal foils into a whole to obtain a prefabricated composite material, wherein 25 layers of metal foils and 24 layers of ceramic films are stacked into a whole in an ABAB stacking manner;
304) and (3) putting the prefabricated composite material into a hot pressing furnace filled with nitrogen, and carrying out hot pressing to obtain the fiber reinforced metal matrix composite material (sample 2), wherein the hot pressing temperature is 600 ℃, the hot pressing pressure is 10MPa, and the pressure maintaining time is 30 min. The properties of sample 3 are shown in Table 1.
The difference between the first embodiment, the second embodiment and the third embodiment is only that the number of layers of the prefabricated composite material is different, the coefficient of thermal expansion and the thermal conductivity of the first embodiment, the second embodiment and the third embodiment are higher than those of the comparison sample 1, which shows that the fiber reinforced metal matrix composite material obtained by the invention has high temperature resistance and thermal conductivity, the coefficient of thermal expansion and the thermal conductivity of the first embodiment, the second embodiment and the third embodiment can be adjusted and controlled by changing the number of layers, and the number of layers can be selected according to the requirements of customers.
Example four
A fiber reinforced metal matrix composite (sample 4) was prepared comprising the following preparation steps:
401) selecting concentrated aluminum carboxylate sol, and setting electrostatic spinning parameters as follows: collecting the solution with the collection distance of 12cm, the voltage of 12kv, the solution feeding speed of 1.8ml/h and the rotating speed of 1800rpm of a roller collector to prepare and obtain a ceramic film with the thickness of 20 microns; selecting 20 μm metal foil;
402) cleaning the metal foil by ultrasonic waves, repeatedly washing the metal foil by deionized water after cleaning until the water is neutral, and airing for 2 hours for later use; soaking the ceramic film in absolute alcohol for 30min, repeatedly washing the ceramic film with deionized water to be neutral after soaking, and airing for 1h for later use;
403) coating 10 mass percent of silicon formate on the upper surface and the lower surface of each ceramic film and each metal foil, and sequentially and alternately stacking the ceramic films and the metal foils into a whole to obtain a prefabricated composite material, wherein 11 layers of metal foils and 10 layers of ceramic films are stacked into a whole in an ABAB stacking mode;
404) and (3) putting the prefabricated composite material into a hot pressing furnace filled with nitrogen, and carrying out hot pressing to obtain the fiber reinforced metal matrix composite material (sample 4), wherein the hot pressing temperature is 650 ℃, the hot pressing pressure is 10MPa, and the pressure maintaining time is 30 min.
The properties of sample 4 are shown in Table 1.
EXAMPLE five
A fiber reinforced metal matrix composite (sample 5) is prepared, the difference between the sample 5 and the sample 1 is only the selection of an adhesive, the adhesive is an epoxy resin solution with the mass fraction of 10%, and the performance of the sample 5 is shown in table 1.
Compared with the sample 1, the samples 4 and 5 change the types of the adhesives, and the data in table 1 show that the types of the adhesives have little influence on the performance of the samples.
EXAMPLE six
A fiber reinforced metal matrix composite (sample 6) was prepared, sample 6 differing from the sample only in that a 50 μm metal foil was selected; the properties of sample 6 are shown in Table 1, and the high temperature resistance of sample 6 is slightly reduced compared to sample 1, but still higher than the control.
TABLE 1 physical Properties of fiber reinforced Metal matrix composites
| Serial number | Coefficient of thermal expansion (K)-1) | Thermal conductivity (W.m)-1·K-1) |
| Control sample | 60×10-6 | 198 |
| Sample 1 | 8.1×10-6 | 233 |
| Sample 2 | 7.5×10-6 | 244 |
| Sample 3 | 8.3×10-6 | 229 |
| Sample No. 4 | 8.0×10-6 | 234 |
| Sample No. 5 | 8.2×10-6 | 237 |
| Sample No. 6 | 9.2×10-6 | 206 |
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.
Claims (10)
1. A preparation method of a fiber reinforced metal matrix composite material is characterized by comprising the following steps: the preparation method comprises the following preparation steps:
alternately adhering ceramic membranes and metal foils into a whole through an adhesive to obtain a prefabricated composite material, wherein the metal foils are N layers, the ceramic membranes are N-1 layers, and N is more than or equal to 2;
and putting the prefabricated composite material into a mould, and carrying out hot pressing in a hot pressing furnace to obtain the fiber reinforced metal matrix composite material.
2. The method of preparing a fiber-reinforced metal matrix composite according to claim 1, wherein: the thickness of the prefabricated composite material is 0.42mm-10 mm.
3. The method of preparing a fiber-reinforced metal matrix composite according to claim 1, wherein: preparing a ceramic film by adopting electrostatic spinning with the thickness of 0.02mm-0.1 mm; the thickness of the metal foil is 0.02mm-0.1 mm.
4. The method of preparing a fiber-reinforced metal matrix composite according to claim 1, wherein: in the hot pressing process, hot pressing is performed under an inert atmosphere.
5. The method of preparing a fiber-reinforced metal matrix composite according to claim 1, wherein: the ceramic film is made of at least one of an alumina ceramic film, a zirconia ceramic film, a barium titanate ceramic film, a silica ceramic film or a magnesia ceramic film.
6. The method of preparing a fiber-reinforced metal matrix composite according to claim 1, wherein: the binder comprises at least one of hydroxypropyl methyl cellulose, silica sol, PVA solution, starch, hydroxy aluminum sol, tetrahydrofuran, cyanoacrylate, vegetable oil, rosin, dextrin, water glass and furan resin.
7. The method of preparing a fiber-reinforced metal matrix composite according to claim 1, wherein: hot pressing is carried out by adopting a hot pressing furnace, and the technological parameters of the hot pressing furnace are that the hot pressing temperature is 100-.
8. The method of preparing a fiber-reinforced metal matrix composite according to claim 1, wherein: the inert gas is one or more of nitrogen, argon, helium, neon and xenon.
9. The method of preparing a fiber-reinforced metal matrix composite according to claim 2, wherein: in the preparation process of the ceramic film, an electrostatic spinning process is adopted for preparation, and the electrostatic spinning parameters are as follows: the collection distance is 10-15cm, the voltage is 10-18kv, the solution feeding speed is 1.8-2ml/h, and the rotation speed of the roller collector is 1800 and 2000 rpm.
10. A fiber-reinforced metal-matrix composite material obtained based on the method for preparing a fiber-reinforced metal-matrix composite material according to any one of claims 1 to 9.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114921734A (en) * | 2022-05-12 | 2022-08-19 | 厦门大学 | Preparation method of continuous ceramic fiber reinforced aluminum matrix composite |
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| US4338132A (en) * | 1978-09-27 | 1982-07-06 | Sumitomo Chemical Company, Limited | Process for fabricating fiber-reinforced metal composite |
| US5280819A (en) * | 1990-05-09 | 1994-01-25 | Lanxide Technology Company, Lp | Methods for making thin metal matrix composite bodies and articles produced thereby |
| US5454403A (en) * | 1993-02-03 | 1995-10-03 | The United States Of America As Represented By The Secrtary Of The Air Force | Weaving method for continuous fiber composites |
| US5460774A (en) * | 1993-12-15 | 1995-10-24 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Method of manufacturing axisymmetric components made of a composite material having a metallic matrix |
| CN109572091A (en) * | 2018-12-12 | 2019-04-05 | 中国航空制造技术研究院 | The preparation method of continuous filament reinforced metallic matrix composite |
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| US4338132A (en) * | 1978-09-27 | 1982-07-06 | Sumitomo Chemical Company, Limited | Process for fabricating fiber-reinforced metal composite |
| US5280819A (en) * | 1990-05-09 | 1994-01-25 | Lanxide Technology Company, Lp | Methods for making thin metal matrix composite bodies and articles produced thereby |
| US5454403A (en) * | 1993-02-03 | 1995-10-03 | The United States Of America As Represented By The Secrtary Of The Air Force | Weaving method for continuous fiber composites |
| US5460774A (en) * | 1993-12-15 | 1995-10-24 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Method of manufacturing axisymmetric components made of a composite material having a metallic matrix |
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| CN114921734A (en) * | 2022-05-12 | 2022-08-19 | 厦门大学 | Preparation method of continuous ceramic fiber reinforced aluminum matrix composite |
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