CN114000069B - Preparation method of continuous SiC fiber reinforced metal matrix composite lattice structure - Google Patents
Preparation method of continuous SiC fiber reinforced metal matrix composite lattice structure Download PDFInfo
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- CN114000069B CN114000069B CN202111176187.7A CN202111176187A CN114000069B CN 114000069 B CN114000069 B CN 114000069B CN 202111176187 A CN202111176187 A CN 202111176187A CN 114000069 B CN114000069 B CN 114000069B
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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
- C22C47/02—Pretreatment of the fibres or filaments
- C22C47/04—Pretreatment of the fibres or filaments by coating, e.g. with a protective or activated covering
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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
- C22C47/02—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
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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
- C22C47/14—Making alloys containing metallic or non-metallic fibres or filaments by powder metallurgy, i.e. by processing mixtures of metal powder and fibres or filaments
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- 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
- C22C49/02—Alloys containing metallic or non-metallic fibres or filaments characterised by the matrix material
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- 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
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Abstract
The invention relates to a preparation method of a continuous SiC fiber reinforced metal matrix composite lattice structure, which utilizes the characteristics that polymethyl methacrylate (PMMA) can be softened, melted and solidified at medium and low temperature (270 ℃) and can be completely cracked into gas at medium and low temperature (400 ℃), SiCf-metal precursor filament belts are soaked in PMMA molten liquid, uniformly distributed precursor filament belts can be obtained after solidification, the precursor filament belts are alternately distributed and heated and pressurized, so that the precursor filaments are mutually contacted and are fixed in relative position under the action of pressure, the PMMA is cracked and gasified by further heating, meanwhile, a multi-cavity structure is favorable for the volatilization of cracked gas, then the temperature is raised to a certain temperature, and the precursor filaments are mutually diffused and connected to form a whole body by pressurization, thereby obtaining the lattice structure. The lattice structure prepared by the method has the advantages that the spacing between the precursor wires is uniform and controllable, the relative angle of the precursor wires between layers can be adjusted in real time according to the position, and more design structure requirements can be met.
Description
Technical Field
The invention belongs to the technical field of material preparation, and particularly relates to a preparation method of a continuous SiC fiber reinforced metal matrix composite lattice structure.
Background
The lattice material is a novel porous material with regular hole shapes and periodic hole arrangement, and is different from the traditional material in that the lattice material has a changeable ordered microstructure and high porosity, has excellent performances of light weight, high strength, high-efficiency heat dissipation, electromagnetic wave and sound absorption, explosion impact resistance and the like, and has better mechanical properties than metal foam with an unordered microstructure under the same weight, so that the lattice material has great application potential in various fields, such as aerospace, transportation, weaponry, building and the like. The lattice material is usually made of metal material, ceramic material, carbon fiber reinforced resin matrix composite material and the like. The metal material has better formability but can not be used at higher temperature, the carbon fiber reinforced resin matrix composite material is also limited by service temperature and has poorer compression resistance, and the ceramic material can be used at high temperature but has poorer formability, particularly the connection between lattice points.
Therefore, the requirements of use at higher temperature and better formability are met, the characteristics of good metal formability and high-temperature resistance of ceramic are required to be utilized, the ceramic/metal composite material has good design space, wherein the continuous monofilament SiC fiber ceramic fiber has excellent room-high-temperature tensile, compression and shear strength, is suitable for being used as a reinforcement of a metal-based composite material, has larger diameter, good operability and convenient forming, and the titanium alloy has excellent medium-high temperature performance and better formability and has good chemical compatibility with the SiC fiber, so that the continuous SiC fiber reinforced titanium-based composite material lattice structure has better application potential. At present, the process for preparing the continuous SiC fiber reinforced titanium matrix composite lattice structure mainly comprises the steps of designing a precursor wire arrangement auxiliary die, laying precursor wires and then carrying out vacuum hot-press molding. The method is characterized in that the required mould is complex, and each layer of precursor wires and the adjacent precursor wires on the upper layer and the lower layer have only one fixed relative angle.
Disclosure of Invention
In order to overcome the defects of complex auxiliary die for laying precursor wires, relatively single arrangement angle of the precursor wires and the like required by preparing a continuous SiC fiber reinforced metal matrix composite lattice structure, the invention aims to provide a preparation process of the SiC fiber reinforced metal matrix composite lattice structure, which can simplify the auxiliary die required by the preparation process, and can adjust and change the arrangement angle of the precursor wires.
In order to achieve the purpose, the invention adopts the following technical scheme:
a preparation method of a continuous SiC fiber reinforced metal matrix composite lattice structure is characterized by comprising the following steps:
step one, cutting continuous SiC f A metallic precursor wire, resulting in a precursor wire ribbon consisting of a set of precursor wires arranged in parallel and uniformly spaced, in particular by depositing continuous SiC f The metal precursor wires are wound outside the cylinder, the relative spacing of the precursor wires is fixed, and then the precursor wire belts are cut along the generatrix of the cylinder, so that the uniformity and the efficiency can be improved. The center distance between adjacent precursor wires can be controlled between 0.2mm and 3mm by controlling the winding pitch according to the design requirements, and can be adjusted according to the specific design requirements. Wherein the continuous SiC f The metal precursor wire is SiC fiber with a coating of metal or alloy thereof with the thickness of 20-100 mu m on the surface. The metal may be selected from titanium, copper, iron, nickel, aluminum, magnesium, tungsten, or the like.
Step two, soaking the precursor filament band prepared in the step one in polymethyl methacrylate molten liquid to obtain a single-layer precursor filament plate after solidification; specifically, the precursor silk ribbon in the first step can be placed in a groove with a predetermined depth and fixed; heating polymethyl methacrylate (PMMA) to a molten state, pouring the molten PMMA into the groove until the precursor filament band is completely immersed, and solidifying the polymethyl methacrylate after cooling to fix the relative position of the precursor filament to obtain the single-layer precursor filament plate. When the continuous SiC is f When the metal precursor wire is a SiC fiber with the diameter of 100 microns and the surface of which is provided with a coating of metal or alloy thereof with the thickness of 20 microns to 100 microns, the preset depth of the groove can be 0.15 mm to 0.5 mm.
Step three, repeating the step two or synchronously preparing a precursor wire plate by adopting a plurality of grooves to prepare a plurality of precursor wire plates;
step four, stacking the precursor wire plates prepared in the step three, wherein precursor wires in two adjacent layers of precursor wire plates are arranged at a certain angle; the angle is generally 20-90 degrees, depending on the design requirements.
Step five, placing the precursor wire plates stacked together in the step four in a vacuum hot-pressing furnace, applying pressure of 0.01-0.5 MPa, and vacuumizing to 10 DEG -2 Pa, heating to 180-200 ℃, heating for 2-3 h, and heatingIn the process, PMMA is softened and melted, heat preservation and pressure maintenance are carried out for 1 to 3 hours, and the pressure action enables the SiC between layers f -the metallic precursor wires reach a state of mutual contact; heating to 270-400 ℃, keeping the temperature and the pressure for 4-6 h, and completely cracking PMMA into gas at the temperature; and then heating to a temperature 0.4-0.8 times of the melting point of the metal (when the metal is titanium, 700-1000 ℃ (determined by titanium alloy brand)), pressurizing to 0.5-40 MPa, preserving heat and pressure for 2-10 h to ensure that the precursor wires which are contacted are mutually diffused and connected into a whole, cooling the furnace to be lower than 200 ℃, and then unloading and taking out to obtain the continuous SiC fiber reinforced metal matrix composite lattice structure.
The invention has the advantages that: (1) in the preparation process, a complex precursor wire laying mold is not needed, the uniform and controllable spacing of precursor wires can be realized, and the PMMA has good light transmittance and can visually check and screen the distribution uniformity and defects of the prepared precursor wire plate; (2) the metal matrix composite material lattice structure has a large number of pores, so that the gas is volatilized after PMMA is cracked; (3) the invention breaks through the limitation of the prior mould method on the fixation and single angle of the interlaminar precursor wires, the arrangement angle of the interlaminar precursor wires is more flexible, and the design requirements can be more flexibly met; (4) the metal matrix composite lattice structure obtained by the method has the advantages that the most surface layer is metal or alloy thereof, the metal matrix composite lattice structure is convenient to be connected with other members/structures through welding, and the connecting position has the advantages of high temperature resistance and high strength.
Drawings
FIG. 1 is a schematic diagram of the process of making and stacking precursor filament plates of the present invention;
FIG. 2 is a schematic diagram of a lattice structure prepared by the method of the present invention.
Detailed Description
For a clearer understanding of the objects, technical solutions and advantages of the present invention, the present invention will be described in further detail below with reference to the accompanying drawings and embodiments.
The invention provides a preparation method of a continuous SiC fiber reinforced metal matrix composite lattice structure, wherein FIG. 1 is a schematic diagram of a preparation and stacking process of a precursor wire plate of the invention, and FIG. 2 is a schematic diagram of the lattice structure prepared by the method of the invention.
Attaching double-sided adhesive tape to the bus direction of the outer cylindrical surface outside the cylindrical tool, and bonding SiC f One end of a TC17 precursor wire (SiC fiber with the diameter of 100 mu m and provided with a TC17 titanium alloy coating with the thickness of 25 mu m on the surface) is fixed on the surface of the cylinder tool perpendicular to the double-sided adhesive tape, the SiC fiber is rotated clockwise along the central shaft of the cylinder tool, the diameter and the height of the cylinder can be adjusted, and the circumference of the cylinder, namely the SiC fiber is the circumference of the cylinder f Length of precursor ribbon of TC17, precursor filament winding pitch set at 0.5mm, SiC wound after winding to specified width f The TC17 precursor wire is fixed by double-sided adhesive, as shown in fig. 1 (a). All the wound SiC f The precursor wire of-TC 17 is cut along the direction of the double-sided adhesive tape (i.e. the generatrix direction of the outer cylindrical surface) to obtain SiC f TC17 precursor band, in this way SiC f The precursor filaments of the precursor filament band of-TC 17 are uniformly arranged and have high efficiency.
Placing the precursor silk ribbon in a groove with the depth of 0.3mm and fixing, as shown in figure 1 (b); heating PMMA to 200 ℃ to be in a molten state, pouring the molten liquid into the groove until the precursor silk ribbon is completely immersed, cooling, solidifying PMMA and carrying out SiC f Fixing the relative position of the-TC 17 precursor wires to prepare single-layer SiC f -TC17 precursor filament plate;
repeating the previous step or preparing a plurality of SiC by adopting a plurality of grooves f -TC17 precursor filament plate.
Mixing SiC f The TC17 precursor wire plates are stacked in a vacuum hot-pressing furnace, and the laying angle is alternatively distributed from 0 degrees/45 degrees/90 degrees, and the schematic diagram is shown in figure 1 (c). Applying a load of 0.1MPa for pre-pressurizing, and vacuumizing to 10 DEG -2 Pa, heating to 200 ℃, keeping the temperature and the pressure for 2h, softening and melting PMMA in the heating process, and enabling SiC between layers to be under the action of pressure f The TC17 precursor filaments reach a state of contact, i.e. the relative position between the precursor filaments has been fixed; heating to 400 ℃, preserving heat and pressure for 6h, completely cracking PMMA into gas at the temperature, and only remaining the precursor filaments with fixed positions; then heating to 900 ℃, pressurizing to 10MPa, preserving heat and pressure for 5h to ensure that precursor wires which are contacted mutually diffuse and connect to form a whole, then cooling in a furnace to be lower than 200 ℃, then unloading and taking out to prepare the continuous SiC fiber reinforced TC17 composite material lattice junctionThe schematic diagram is shown in FIG. 2.
Although the TC17 titanium alloy is exemplified above, titanium or other titanium alloy may be used instead, or even other metals or alloys thereof, in which case the temperature required to form the diffusion bond between the contacting precursor wires is typically 0.4 to 0.8 times the melting point of the corresponding metal or alloy.
According to the invention, by utilizing the characteristics that polymethyl methacrylate (PMMA) can be softened, melted and solidified at medium and low temperature (-270 ℃) and can be completely cracked into gas at medium and low temperature (-400 ℃), SiCf-metal precursor ribbons are soaked in PMMA molten liquid, uniformly distributed precursor ribbons can be obtained after solidification, the precursor ribbons are alternately distributed and heated and pressurized, so that the precursor ribbons are mutually contacted and are fixed in relative position under the action of pressure, the PMMA is cracked and gasified by further heating, meanwhile, the porous structure is favorable for volatilization of cracked gas, then the temperature is raised to a certain temperature, and the precursor ribbons are mutually diffused and connected to form a whole body by pressurization, thereby obtaining the lattice structure. The lattice structure prepared by the method has the advantages that the spacing between the precursor wires is uniform and controllable, the relative angle of the precursor wires between layers can be adjusted in real time according to the position, and more design structure requirements can be met.
Claims (9)
1. A preparation method of a continuous SiC fiber reinforced metal matrix composite lattice structure comprises the following steps:
step one, cutting continuous SiC f -a metallic precursor wire, obtaining a precursor wire ribbon consisting of a set of precursor wires arranged in parallel and evenly spaced;
step two, soaking the precursor filament band prepared in the step one in polymethyl methacrylate molten liquid to obtain a single-layer precursor filament plate after solidification;
step three, repeating the step two to prepare a plurality of precursor wire plates;
step four, stacking the precursor wire plates prepared in the step three, wherein precursor wires in two adjacent layers of precursor wire plates are arranged at a certain angle;
placing the precursor wire plates stacked together in the fourth step into a vacuum hot pressing furnace, applying a pressure of 0.01-0.5 MPa, heating to 180-200 ℃, keeping the temperature and the pressure for more than 2h, and keeping the temperature and the pressure for more than 1 h; then heating to 270-400 ℃, and keeping the temperature and pressure for more than 4 h; then heating to the temperature 0.4-0.8 times of the melting point of the metal, pressurizing to 0.5-40 MPa, and preserving heat and pressure for 2-10 h; and (4) unloading and taking out after the furnace is cooled to be lower than 200 ℃ to obtain the continuous SiC fiber reinforced metal matrix composite lattice structure.
2. The method of claim 1, wherein the continuous SiC f The metal precursor wire is SiC fiber with a coating of metal or alloy thereof with the thickness of 20-100 mu m on the surface.
3. The method of claim 2, wherein the metal is selected from the group consisting of titanium, copper, iron, nickel, aluminum, magnesium, and tungsten.
4. The method of claim 1, wherein said trimming of continuous SiC f -a metallic precursor wire, obtaining a precursor wire ribbon consisting of a set of parallel uniformly arranged precursor wires comprising applying a continuous SiC ribbon f Winding the metal precursor wires on the outer side of the cylinder, fixing the relative spacing of the precursor wires, and then cutting along a generatrix of the cylinder to obtain the precursor wire belt.
5. The method according to claim 1, wherein the step of solidifying the precursor ribbon obtained in the step one by dipping the precursor ribbon in the molten polymethyl methacrylate to obtain a single-layered precursor ribbon comprises the steps of placing and fixing the precursor ribbon in the step one in a groove with a predetermined depth; heating polymethyl methacrylate to a molten state, pouring the molten polymethyl methacrylate into the groove until the precursor silk ribbon is completely immersed, cooling, solidifying the polymethyl methacrylate, and fixing the relative position of the precursor silk to obtain the single-layer precursor silk plate.
6. The method of claim 5, wherein the continuous SiC f The metal precursor wire is a SiC fiber with the diameter of 100 mu m and the surface of which is provided with a coating of metal or alloy thereof with the thickness of 20 mu m to 100 mu m, and the preset depth of the groove is 0.15 mm to 0.5 mm.
7. A method according to claim 1 wherein the centre distance between adjacent precursor filaments is from 0.2mm to 3 mm.
8. A method according to claim 1, wherein the angle between the precursor filaments in two adjacent precursor filament sheets is from 20 ° to 90 °.
9. The process according to claim 1, wherein the temperature rise time to 180 ℃ to 200 ℃ is 2 to 3 hours, the heat and pressure retention time is 1 to 3 hours, and the heat and pressure retention time at 270 ℃ to 400 ℃ is 4 to 6 hours.
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102277544A (en) * | 2011-08-22 | 2011-12-14 | 中国科学院金属研究所 | SiCf/Ti-based composite material 0/90-degree laminated thin plate with designable strength and weldability and preparation method thereof |
| CN110248912A (en) * | 2017-02-02 | 2019-09-17 | 赛峰集团陶瓷 | A method of manufacture composite material component |
| CN110527933A (en) * | 2019-10-16 | 2019-12-03 | 中国航空制造技术研究院 | A kind of preparation method of titanium composite material thermal protection stressed-skin construction |
| CN111575611A (en) * | 2020-06-19 | 2020-08-25 | 南京尚吉增材制造研究院有限公司 | SiC fiber-WC-Ni hard alloy composite material and preparation method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102925825A (en) * | 2012-11-16 | 2013-02-13 | 中国航空工业集团公司北京航空制造工程研究所 | Preparation method for continuous fiber reinforced titanium-titanium aluminum hybrid matrix composite material |
| CN106521369A (en) * | 2016-11-29 | 2017-03-22 | 中国科学院金属研究所 | Dense precursor belt of SiC fiber-reinforced titanium-based composite and preparation method of dense precursor belt |
| US10752554B1 (en) * | 2019-11-21 | 2020-08-25 | Raytheon Technologies Corporation | Intermetallic matrix composite |
| CN112517910A (en) * | 2020-11-13 | 2021-03-19 | 西安理工大学 | Method for improving strength of high-porosity layered porous titanium and titanium alloy |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102277544A (en) * | 2011-08-22 | 2011-12-14 | 中国科学院金属研究所 | SiCf/Ti-based composite material 0/90-degree laminated thin plate with designable strength and weldability and preparation method thereof |
| CN110248912A (en) * | 2017-02-02 | 2019-09-17 | 赛峰集团陶瓷 | A method of manufacture composite material component |
| CN110527933A (en) * | 2019-10-16 | 2019-12-03 | 中国航空制造技术研究院 | A kind of preparation method of titanium composite material thermal protection stressed-skin construction |
| CN111575611A (en) * | 2020-06-19 | 2020-08-25 | 南京尚吉增材制造研究院有限公司 | SiC fiber-WC-Ni hard alloy composite material and preparation method thereof |
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