CN114645226B - Unidirectional laminated structure carbon fiber reinforced silicon carbide/aluminum-based composite material and preparation method thereof - Google Patents

Unidirectional laminated structure carbon fiber reinforced silicon carbide/aluminum-based composite material and preparation method thereof Download PDF

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CN114645226B
CN114645226B CN202011522023.0A CN202011522023A CN114645226B CN 114645226 B CN114645226 B CN 114645226B CN 202011522023 A CN202011522023 A CN 202011522023A CN 114645226 B CN114645226 B CN 114645226B
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silicon carbide
carbon fiber
aluminum alloy
composite material
unidirectional
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CN114645226A (en
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陈照峰
李远豪
杨丽霞
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Nanjing University of Aeronautics and Astronautics
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Nanjing University of Aeronautics and Astronautics
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    • 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
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
    • C23C14/14—Metallic material, boron or silicon
    • C23C14/18—Metallic material, boron or silicon on other inorganic substrates
    • C23C14/185—Metallic material, boron or silicon on other inorganic substrates by cathodic sputtering
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/22—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
    • C23C14/34—Sputtering
    • C23C14/35—Sputtering by application of a magnetic field, e.g. magnetron sputtering
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C16/00—Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes
    • C23C16/22—Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the deposition of inorganic material, other than metallic material
    • C23C16/26—Deposition of carbon only
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C16/00—Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes
    • C23C16/22—Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the deposition of inorganic material, other than metallic material
    • C23C16/30—Deposition of compounds, mixtures or solid solutions, e.g. borides, carbides, nitrides
    • C23C16/32—Carbides

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Inorganic Chemistry (AREA)
  • General Chemical & Material Sciences (AREA)
  • Manufacture Of Alloys Or Alloy Compounds (AREA)

Abstract

The invention discloses a carbon fiber reinforced silicon carbide/aluminum-based composite material with a unidirectional laminated structure and a preparation method thereof, wherein the composite material consists of unidirectional carbon fiber cloth, a pyrolytic carbon interface layer, silicon carbide and an aluminum alloy matrix, and the density of the composite material is 1.8-2.5 g/cm 3 The tensile strength is 300-450 MPa; the silicon carbide matrix can improve the tolerance temperature of the composite material, and can reduce the residual thermal stress caused by the difference of the thermal expansion coefficients between the carbon fiber and the aluminum alloy matrix; the aluminum alloy substrate prepared by magnetron sputtering can improve the wettability between the aluminum alloy and the silicon carbide and effectively improve the interface bonding strength of the aluminum alloy and the silicon carbide; the diffusion bonding can enable the aluminum alloy matrix to be better filled into the pores, so that the compactness of the composite material is improved, and the tensile strength of the composite material is improved.

Description

Carbon fiber reinforced silicon carbide/aluminum matrix composite material with unidirectional laminated structure and preparation method thereof
Technical Field
The invention relates to a carbon fiber reinforced silicon carbide/aluminum matrix composite material with a unidirectional laminated structure and a preparation method thereof.
Background
The fiber reinforced ceramic matrix composite has low density, high specific strength, corrosion resistance and high temperature resistance, and is widely applied to the fields of aerospace, satellites and the like. However, due to the limitation of the preparation process, the properties of the ceramic matrix composite are unstable due to the existence of defects such as pores, microcracks and the like, and the fracture toughness of the ceramic matrix composite still needs to be further improved.
The fiber reinforced aluminum matrix composite has high specific strength, high specific rigidity and good impact resistance, and is widely applied to the fields of aerospace, satellites and the like. However, the service environment is usually harsh, and the aluminum alloy substrate is softened at high temperature (300 ℃), and the rigidity is seriously reduced, so that the requirements of various aspects cannot be met.
The aluminum alloy has low melting temperature and low viscosity in a molten state, and can be effectively filled into pores and defects of the fiber reinforced ceramic matrix composite, so that the load transfer capability is improved, and the crack source is effectively reduced to reduce the occurrence of stress concentration. The aluminum alloy has the advantages of high specific strength, high specific modulus, good impact resistance and good plasticity, has lower viscosity and lower melting temperature (less than 800 ℃) in a molten state, and can be effectively filled into pores and cracks of the fiber reinforced ceramic matrix composite material, thereby reducing crack generation sources and improving load transfer capacity.
The fiber reinforced double-matrix composite material is prepared by taking the carbon fiber preform as a framework and taking silicon carbide and aluminum alloy as matrixes, so that the defect of the high-temperature performance of the fiber reinforced aluminum matrix composite material can be overcome, and the defect of the fracture toughness and the plasticity of the fiber reinforced ceramic matrix composite material can be overcome. In addition, aluminum alloys and carbon fibers have large differences in thermal expansion coefficients and poor wettability, which also affects the properties.
The Chinese invention patent with the application publication number of CN106478125A discloses a B 4 The preparation method of the C modified C/C-SiC brake material adopts a vacuum pressure impregnation method to mix B 4 Introducing the powder C to the density of 0.4-0.6 g/cm 3 And (3) preparing the C/C-SiC brake material by chemical vapor infiltration and reaction melt infiltration in the three-dimensional needled carbon felt.
The Chinese patent with application publication number CN105818476A discloses a surface modified three-dimensional network carbon fiber reinforced composite material and a preparation method thereof, wherein the surface of a three-dimensional carbon fiber framework is pretreated, and then diamond, carbon nano tubes and graphene are deposited through chemical vapor, and then metal or polymer is carried out, so that the carbon fiber reinforced metal-based or polymer-based composite material with a three-dimensional network framework structure is obtained.
Although the performance of the modified ceramic matrix composite material or the ceramic modified metal material can be improved, the interface compatibility of two different materials of ceramic and metal is not improved, and the porosity and the defects in the ceramic matrix composite material are not effectively reduced, so that the performance of the ceramic matrix composite material and the alloy material cannot be really exerted, and the toughening and reinforcing effects of the alloy on the ceramic matrix composite material cannot be exerted.
Disclosure of Invention
In order to solve the problems, the invention provides the carbon fiber reinforced silicon carbide/aluminum-based composite material with the unidirectional laminated structure and the preparation method thereof, which effectively improve the interface compatibility of the ceramic-based composite material and the aluminum alloy and improve the bonding strength and the bonding stability of the aluminum alloy and the ceramic-based composite material.
A unidirectional laminated structure carbon fiber reinforced silicon carbide/aluminum matrix composite material and a preparation method thereof are characterized by comprising the following steps in sequence:
(1) Ultrasonically cleaning and drying the unidirectional carbon fiber cloth by using absolute ethyl alcohol;
(2) Preparing a pyrolytic carbon interface layer in the dried fiber cloth by adopting a chemical vapor infiltration method, wherein the flow ratio of propylene to argon is 60: 150, and the deposition temperature is 800-1000 ℃; then filling a silicon carbide matrix in situ at 1100-1200 ℃ in the prepared unidirectional carbon fiber cloth with the pyrolytic carbon interface layer by using a chemical vapor infiltration method, wherein the flow ratio of trichloromethylsilane, hydrogen and argon is 20: 200, and obtaining a fiber/silicon carbide matrix preformed body;
(3) Depositing aluminum alloy in the fiber/silicon carbide substrate preformed body by adopting a magnetron sputtering method, wherein the target material is aluminum alloy; the pressure of the chamber is reduced to 10 by adopting diffusion pump for vacuum pumping -3 Pa, maintaining the pressure of argon in the chamber at 0.3Pa in the deposition process; after the deposition of each layer of unidirectional carbon fiber cloth is finished, the front side and the back side of the deposition are reversed, and secondary deposition is carried out;
(4) Preparing unidirectional carbon fiber cloth into a laminated structure, and preparing a blank after diffusion bonding of an aluminum alloy matrix under certain pressure and temperature; the pressure is 40-90 MPa, and the temperature is 600-700 ℃.
The invention has the beneficial effects that: (1) The preparation method of the selected matrix is beneficial to the stability and uniformity of the microstructure of the prepared composite material and the improvement of the combination property of the two matrixes; (2) The composite material has low density, high strength, high rigidity, good fracture toughness, good impact resistance and low defect sensitivity, and is an important candidate advanced composite material in the aerospace field; (3) the composite material has excellent tensile strength.
Example of the implementation
Example 1: ultrasonically cleaning and drying unidirectional carbon fiber cloth with the thickness of 0.2mm by using absolute ethyl alcohol; preparing a pyrolytic carbon interface layer in the dried fiber, wherein the reaction temperature is 900 ℃; then filling a silicon carbide substrate in situ in the prepared unidirectional carbon fiber cloth with the pyrolytic carbon interface layer, wherein the reaction temperature is 1100 ℃, and obtaining a fiber/silicon carbide substrate preformed body; depositing aluminum alloy in the fiber/silicon carbide substrate preformed body, wherein the target material is 2 series aluminum alloy; preparing 30 layers of unidirectional carbon fiber cloth with deposited pyrolytic carbon, silicon carbide and aluminum alloy into a laminated structure, and performing diffusion bonding on the aluminum alloy at 50MPa and 600 ℃ to obtain a blank; and (3) obtaining a tensile sample after mechanical processing, and performing a tensile test on an electronic universal testing machine, wherein the tensile strength is 350 +/-50 MPa.
Example 2: ultrasonically cleaning a 0.4mm thick unidirectional carbon fiber cloth by using absolute ethyl alcohol and drying; preparing a pyrolytic carbon interface layer in the dried fiber, wherein the reaction temperature is 1000 ℃; then filling a silicon carbide substrate in situ in the prepared unidirectional carbon fiber cloth with the pyrolytic carbon interface layer, wherein the reaction temperature is 1200 ℃, and obtaining a fiber/silicon carbide substrate preformed body; depositing aluminum alloy in the fiber/silicon carbide substrate preformed body, wherein the target material is 7 series aluminum alloy; preparing 15 layers of unidirectional carbon fiber cloth deposited with pyrolytic carbon, silicon carbide and aluminum alloy into a laminated structure, and performing diffusion bonding on the aluminum alloy at 80MPa and 650 ℃ to obtain a blank; and (4) obtaining a tensile sample after mechanical processing, and performing a tensile test on an electronic universal testing machine, wherein the tensile strength is 400 +/-30 MPa.

Claims (1)

1. The carbon fiber reinforced silicon carbide/aluminum-based composite material with the unidirectional laminated structure has the density of 1.8-2.5 g/cm 3 The tensile strength is 300-450 Mpa, and the composite material consists of unidirectional carbon fiber cloth, a pyrolytic carbon interface layer, silicon carbide and aluminum alloy, and is characterized in that the pyrolytic carbon interface layer, the silicon carbide and the aluminum alloy matrix are deposited on the unidirectional carbon fiber cloth with the thickness of 0.05-0.5 mm in sequence, then the pyrolytic carbon interface layer, the silicon carbide and the aluminum alloy matrix are made into a laminated structure and are hot-pressed to obtain a blank, and a final finished product is obtained after machining; the volume fraction of the carbon fiber is 20-35%, the thickness of the pyrolytic carbon interface layer is 0.1-0.8 μm, and the volume fraction of the aluminum alloy matrix is 20-30%; the preparation method comprises the following steps in sequence:
(1) Ultrasonically cleaning and drying the unidirectional carbon fiber cloth by using absolute ethyl alcohol;
(2) Preparing a pyrolytic carbon interface layer in the purified unidirectional carbon fiber cloth by adopting a chemical vapor infiltration method, wherein the flow ratio of propylene to argon is 60: 150, and the deposition temperature is 800-1000 ℃; then filling a silicon carbide matrix in situ at 1100-1200 ℃ in the prepared unidirectional carbon fiber cloth with the pyrolytic carbon interface layer by using a chemical vapor infiltration method, wherein the flow ratio of trichloromethylsilane, hydrogen and argon is 20: 200, and obtaining a fiber/silicon carbide matrix preformed body;
(3) Depositing aluminum alloy in the fiber/silicon carbide substrate preformed body by adopting a magnetron sputtering method, wherein the target material is aluminum alloy; the pressure of the chamber is reduced to 10 by adopting a diffusion pump to vacuumize -3 Pa, keeping the pressure of argon in the chamber at 0.3Pa in the deposition process; after the deposition of each layer of unidirectional carbon fiber cloth is finished, the front side and the back side of the deposition are reversed, and secondary deposition is carried out;
(4) Preparing unidirectional carbon fiber cloth into a laminated structure, and performing diffusion bonding on an aluminum alloy matrix under certain pressure and temperature to obtain a blank; the pressure is 40-90 MPa, and the temperature is 600-700 ℃.
CN202011522023.0A 2020-12-21 2020-12-21 Unidirectional laminated structure carbon fiber reinforced silicon carbide/aluminum-based composite material and preparation method thereof Active CN114645226B (en)

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