Continuous boron fiber reinforced aluminum alloy matrix composite and method of making same

Abstract

The application belongs to the technical field of aerospace materials, and provides a continuous boron fiber reinforced aluminum alloy matrix composite material, which is prepared by laying and hot isostatic pressing of boron fiber precursor filaments; the boron fiber precursor filaments comprise boron fiber filaments, a B4C layer, a Ti layer and an aluminum alloy layer which are sequentially deposited on the boron fiber filaments. The application introduces a B4C / Ti double coating layer on the boron fiber filaments, improves the interface bonding strength between the reinforcing boron fiber and the aluminum alloy matrix, and also maintains the integrity of the boron fiber; so that the interface bonding strength and the tensile strength of the continuous boron fiber reinforced aluminum alloy matrix composite material are significantly improved. f Compared with the interface bonding strength and the tensile strength of the B4C / Al matrix composite material without introducing the B4C / Ti double coating layer, the interface bonding strength and the tensile strength of the continuous boron fiber reinforced aluminum alloy matrix composite material are significantly improved, which has important significance for meeting the strong demand for lightweight high-strength materials in the field of aerospace.

Description

Technical Field

[0001] This invention relates to the field of aerospace materials technology, and in particular to continuous boron fiber reinforced aluminum alloy matrix composites and their preparation methods. Background Technology

[0002] Aluminum alloys are widely used in the aerospace field due to their low density, excellent processing performance, good specific strength, and good comprehensive properties, such as structural components like aircraft load-bearing frames, beams, panels, skins, tail fins, and I-beams. With the rapid development of the aerospace industry, more stringent requirements have been placed on the strength and operating temperature of aluminum alloys, especially since the strength of aluminum alloys is highly sensitive to temperature and rapidly decreases at high temperatures. Research shows that introducing ceramic reinforcements into tough metals is an important strategy to improve the mechanical properties of metallic materials. Common reinforcements include particles, whiskers (or short fibers), and continuous fibers. Among them, aluminum matrix composites constructed with SiC particles as reinforcement possess high specific strength, high specific modulus, high wear resistance, and excellent compressive strength and corrosion resistance, and have achieved great success as lightweight structural materials in aerospace, automotive, and construction fields. Compared to SiC particles, bundled carbon fibers used as reinforcement in aluminum matrix composites not only possess excellent properties such as low density, high specific strength, high specific modulus, fatigue resistance, and low coefficient of thermal expansion, but also significantly improve the tensile strength of the composite material. Monofilament CVD (chemical vapor deposition) ceramic fibers (such as SiC fibers) offer higher stiffness while maintaining high strength compared to bundled carbon fibers, further enhancing the tensile and shear properties of composite materials as reinforcements. Compared to SiC fibers, CVD monofilament boron fibers possess superior properties such as high specific strength, specific modulus, and high-temperature resistance, while also exhibiting low density, giving them a significant advantage in achieving lightweighting. Continuous fibers (long fibers) refer to fibers that are a continuous whole; primarily, this means that the fibers used in composite materials are continuous bundles or fabrics. Therefore, continuous boron fibers are ideal reinforcements for aluminum alloys, and the resulting continuous boron fiber reinforced aluminum matrix composites, as novel lightweight and high-strength materials, have significant application value in the aerospace field.

[0003] The properties of continuous boron fiber reinforced aluminum alloy matrix composites mainly depend on the properties of the reinforcing fibers, the metal matrix, and the interfacial reaction zones, especially the interfacial configuration resulting from the interfacial reactions that are closely related to failure modes. Given the relationship between the aluminum matrix and boron fibers (B... f There is a significant mechanical mismatch between the two components, meaning that the wettability between them is poor and the chemical reaction is weak, resulting in low interfacial bonding strength and a substantial reduction in the tensile properties of the composite material. Summary of the Invention

[0004] In view of this, the object of the present invention is to provide a continuous boron fiber reinforced aluminum alloy matrix composite material and a method for preparing the same. The continuous boron fiber reinforced aluminum alloy matrix composite material provided by the present invention has excellent tensile strength.

[0005] To achieve the above-mentioned objectives, the present invention provides the following technical solution:

[0006] This invention provides a continuous boron fiber reinforced aluminum alloy matrix composite material, which is prepared by laying boron fiber precursor filaments and hot isostatic pressing.

[0007] The boron fiber precursor filament comprises a boron fiber monofilament, on which a B4C layer, a Ti layer, and an aluminum alloy layer are sequentially deposited.

[0008] Preferably, the diameter of the boron fiber monofilament is 85–125 μm and the length is 15–20 mm.

[0009] Preferably, the thickness of the B4C layer is 1–4 μm.

[0010] Preferably, the thickness of the Ti layer is 100–1000 nm.

[0011] Preferably, the thickness of the aluminum alloy layer is 15–40 μm.

[0012] This invention also provides a method for preparing the continuous boron fiber reinforced aluminum alloy matrix composite material described above, comprising the following steps:

[0013] Boron fiber precursor filaments were obtained by sequentially depositing a B4C layer, a Ti layer, and an aluminum alloy layer on boron fiber monofilaments using chemical vapor deposition.

[0014] The boron fiber precursor filaments are laid up and hot isostatically pressed to obtain the continuous boron fiber reinforced aluminum alloy matrix composite material.

[0015] Preferably, the deposition parameters of the B4C layer include: the working gas is methane, boron trichloride and hydrogen, the volume ratio of methane, boron trichloride and hydrogen is 2:1:1 to 2:6:5, the DC heating pyrolysis temperature is 800 to 1400°C, and the reaction chamber pressure is atmospheric pressure.

[0016] Preferably, the deposition parameters of the Ti layer include: the cathode target is a Ti metal target, the protective gas is argon, the cavity gas pressure is 0.5 to 1.3 Pa, the bias voltage is -50 to -200 V, the current is 0.2 to 0.8 A, the voltage is 100 to 500 V, and the sputtering time is 6 to 60 min.

[0017] Preferably, the deposition parameters of the aluminum alloy layer include: the cathode target is an aluminum alloy target, the protective gas is argon, the cavity gas pressure is 0.5 to 1.3 Pa, the bias voltage is -50 to -200 V, the current is 1.0 to 3.0 A, the voltage is 100 to 500 V, the deposition rate is 3.0 to 10.0 μm / h, and the sputtering time is 3 to 6 h.

[0018] Preferably, the hot isostatic pressing temperature is 450–750°C, the pressure is 50–200 MPa, and the holding time is 1–4 h.

[0019] This invention provides a continuous boron fiber reinforced aluminum alloy matrix composite material, prepared by layup and hot isostatic pressing of boron fiber precursor filaments. The boron fiber precursor filaments comprise boron fiber monofilaments, on which a B4C layer, a Ti layer, and an aluminum alloy layer are sequentially deposited. This invention introduces a B4C / Ti double coating onto the boron fiber monofilaments, improving the interfacial bonding strength between the reinforcing boron fibers and the aluminum alloy matrix while maintaining the integrity of the boron fibers; resulting in a significant improvement in the interfacial bonding strength and tensile strength of the continuous boron fiber reinforced aluminum alloy matrix composite material. Compared to B4C / Ti composites without the B4C / Ti double coating... f The interfacial bonding strength and tensile strength of the / Al-based composite material are significantly improved, which is of great significance for meeting the strong demand for lightweight and high-strength materials in the aerospace field. Data from the examples show that the tensile strength of the continuous boron fiber reinforced aluminum alloy matrix composite material provided by this invention is 985 MPa. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of magnetron sputtering of the boron fiber precursor filament of the present invention;

[0021] Figure 2 This is a schematic diagram of the preparation method of the continuous boron fiber reinforced aluminum alloy matrix composite material of the present invention;

[0022] Figure 3 B obtained from Comparative Example 1 f / Al alloy precursor wire (a), B obtained from Comparative Example 2 f / B4C / Al alloy precursor wire (b) and B obtained in Example 1 f SEM image of the cross section of the / B4C / Ti / Al alloy precursor wire (c);

[0023] Figure 4 B obtained from Comparative Example 1 f SEM images of cross sections of Al-based composite materials;

[0024] Figure 5 B obtained as a comparative example 2 f SEM images of cross-sections of B4C / Al-based composite materials;

[0025] Figure 6 B obtained in Example 1 f SEM images of cross-sections of / B4C / / Ti / Al-based composite materials;

[0026] Figure 7 B prepared for this invention f Schematic diagram of a tensile specimen and its dimensions of a B4C / Ti / Al based composite material;

[0027] Figure 8 The alloy is aluminum alloy, and the B obtained in Comparative Example 1 is... f / Al-based composite material, B obtained from Comparative Example 2 f / B4C / Al-based composite material and B obtained in Example 1 f Comparison of room temperature tensile strength of / B4C / Ti / Al based composites. Detailed Implementation

[0028] This invention provides a continuous boron fiber reinforced aluminum alloy matrix composite material, which is prepared by laying boron fiber precursor filaments and hot isostatic pressing.

[0029] The boron fiber precursor filament comprises a boron fiber monofilament, on which a B4C layer, a Ti layer, and an aluminum alloy layer are sequentially deposited.

[0030] Unless otherwise specified, all raw materials used in this invention are preferably commercially available products.

[0031] In this invention, the diameter of the boron fiber monofilament is preferably 85–125 μm, and the length is preferably 15–20 mm. In this invention, the boron fiber is preferably tungsten-core boron fiber.

[0032] In this invention, the thickness of the B4C layer is preferably 1 to 4 μm, and more preferably 1.5 to 3 μm.

[0033] In this invention, the thickness of the Ti layer is preferably 100-1000 nm, more preferably 300-800 nm, and even more preferably 500-600 nm.

[0034] In this invention, the thickness of the aluminum alloy layer is preferably 15-40 μm, more preferably 20-35 μm, more preferably 25-30 μm, and most preferably 27 μm. In this invention, the material of the aluminum alloy layer is preferably 6061 aluminum alloy, 2024 aluminum alloy, or 7075 aluminum alloy. In a specific embodiment of this invention, the material of the aluminum alloy is specifically preferably 6061 aluminum alloy.

[0035] In this invention, the parameters for the arrangement and hot isostatic pressing are preferably described in detail in the preparation method section, and will not be repeated here.

[0036] This invention also provides a method for preparing the continuous boron fiber reinforced aluminum alloy matrix composite material described above, comprising the following steps:

[0037] Boron fiber precursor filaments were obtained by sequentially depositing a B4C layer, a Ti layer, and an aluminum alloy layer on boron fiber monofilaments using chemical vapor deposition.

[0038] The boron fiber precursor filaments are laid up and hot isostatically pressed to obtain the continuous boron fiber reinforced aluminum alloy matrix composite material.

[0039] This invention obtains boron fiber precursor filaments by sequentially depositing a B4C layer, a Ti layer, and an aluminum alloy layer on a boron fiber monofilament using chemical vapor deposition.

[0040] In this invention, the deposition parameters of the B4C layer include: the working gas is preferably methane, boron trichloride and hydrogen, the volume ratio of methane, boron trichloride and hydrogen is preferably 2:1:1 to 2:6:5, more preferably 3:4:2, the DC heating pyrolysis temperature is preferably 800 to 1400°C, more preferably 900 to 1200°C, more preferably 1000 to 1100°C, and the reaction chamber pressure is preferably atmospheric pressure.

[0041] After depositing the B4C layer and before depositing the Ti layer, the present invention preferably further includes cleaning; the cleaning is ion sputtering cleaning; the parameters of the ion sputtering cleaning include: the back vacuum degree of the deposition chamber is preferably ≤5×10⁻⁶. -4 Pa, more preferably 5 × 10 Pa -4 Pa; the gas pressure in the coating chamber is preferably 0.2-0.4 Pa, the rotation speed of the suspension frame is preferably 3-9 r / min, more preferably 5-6 r / min, the sputtering gas is preferably argon, the flow rate of the sputtering gas is preferably 40-90 sccm, more preferably 50-80 sccm, more preferably 60-70 sccm, the voltage of the ion source is preferably 700-900 V, more preferably 800-850 V, the current of the ion source is preferably 0.2-0.4 A, more preferably 0.3 A, and the time is preferably 15-40 min, more preferably 20-30 min.

[0042] In this invention, the deposition parameters of the Ti layer include: the cathode target is preferably a titanium metal target, the purity of the titanium metal target is preferably 99.99%, the titanium metal target is preferably placed at a counter-target position, the counter-target surfaces are parallel, and the spacing is preferably 10-35 cm, more preferably 22 cm; the size of the Ti metal target is preferably 150×75×6 mm, the protective gas is preferably argon, the flow rate of the argon gas is preferably 40-90 sccm, and the back gas pressure of the coating chamber is preferably 0.5-1.3 Pa. The preferred step pressure is 0.8–1.0 Pa, the preferred bias voltage is -50–-200 V, more preferably -100 V–-150 V, the preferred current is 0.2–0.8 A, more preferably 0.3–0.6 A, more preferably 0.4–0.5 A, the preferred voltage is 100–500 V, more preferably 200–400 V, more preferably 250–350 V, and the preferred sputtering time is 6–60 min, more preferably 10–50 min, more preferably 20–40 min, and most preferably 30 min.

[0043] In this invention, the deposition parameters of the aluminum alloy layer include: the cathode target is preferably an aluminum alloy target, and the aluminum alloy target is preferably 6061 aluminum alloy, 2024 aluminum alloy, or 7075 aluminum alloy; the size of the aluminum alloy target is preferably 150×75×6mm; the alloy target is preferably placed at a target-aligned position, the target surfaces of the target-aligned positions are parallel, the spacing is preferably 10-35cm, more preferably 22cm; the protective gas is preferably argon; and the back gas pressure of the coating chamber is preferably 0.5-1.3Pa, more preferably... The preferred values ​​are 0.7–1.1 Pa, more preferably 0.8–1.0 Pa; the preferred bias voltage is -50–-200 V, more preferably -100 V–-150 V; the preferred current is 1.0–3.0 A, more preferably 1.5–2.5 A, more preferably 2.0 A; the preferred voltage is 100–500 V, more preferably 200–400 V, more preferably 300–370 V; the preferred deposition rate is 3.0–10.0 μm / h; and the preferred sputtering time is 3–6 h, more preferably 4–5 h.

[0044] In this invention, the deposition of the B4C layer, ion sputtering cleaning, Ti layer, and aluminum alloy layer are preferably performed in a single-wire chemical vapor deposition apparatus. The deposition of the B4C layer, ion sputtering cleaning, Ti layer, and aluminum alloy layer is described in detail below with reference to the single-wire chemical vapor deposition apparatus, preferably including the following steps:

[0045] Boron fiber monofilaments are placed in a monofilament chemical vapor deposition apparatus, and working gas is introduced into the reaction chamber to atmospheric pressure. Then, the working gas is heated to 800-1400°C by direct current to cause a cracking reaction. By controlling the wire feed speed of the boron fiber monofilaments, boron fiber monofilaments with a deposited B4C protective coating are obtained.

[0046] The boron fiber monofilaments with deposited B4C protective coating are evenly arranged on the sample holder and placed on the suspension frame. The surface spacing between adjacent boron fiber monofilaments with deposited B4C protective coating is preferably 0.2-0.7 mm, more preferably 0.5 mm. The magnetron sputtering system cavity cover is opened, and the Ti metal target is installed on one pair of cathode target positions, and the aluminum alloy target is installed on another pair of cathode target positions. The target surfaces are parallel to each other, and the target spacing between the two targets in each pair of cathode target positions is preferably 10-35 cm. The magnetron sputtering system cavity cover is then closed.

[0047] Turn on the mechanical pump and wait for the background vacuum in the coating chamber to reach below 10 Pa. Then turn on the molecular pump to evacuate the vacuum until the background vacuum in the coating chamber is below 5 × 10 Pa. -4 After Pa, turn on the suspension frame rotation switch and set the rotation speed to 3-9 r / min. Introduce sputtering gas argon and adjust the flow rate of sputtering gas argon to 40-90 sccm. Turn on the ion source switch and set the voltage of the ion source to 700-900V and the current to 0.2-0.4A. Clean the boron fiber monofilaments with deposited B4C protective coating. After cleaning for 15-40 minutes, turn off the ion source switch.

[0048] After shutting off the ion source, adjust the argon gas flow rate and gate valve to adjust the chamber gas pressure to 0.5–1.3 Pa, and start sputtering with the Ti metal target; turn on the bias switch and set the parameters to -50–-200 V, apply DC power to the titanium cathode target for sputtering, with a current of 0.2–0.8 A and a voltage of 100–500 V, and open the target baffle after the ignition stabilizes. The sputtering time is 6–60 min, and a Ti coating is deposited on the surface of the boron fiber monofilament with the B4C protective coating.

[0049] After the Ti coating is sputtered, the DC power switch of the titanium metal target is turned off, and the titanium metal target baffle is turned off. Then, the aluminum alloy target sputtering is turned on: the bias parameter is adjusted to -50 to -200V, the voltage intensity is adjusted to 0.5 to 1.3Pa, and DC power is applied to the aluminum alloy cathode target for sputtering. The current is 1.0 to 3.0A, the voltage is 100 to 500V, the aluminum alloy deposition rate is 3.0 to 10.0μm / h, and the sputtering time is 3 to 6 hours, depositing an aluminum alloy coating on the fiber surface with Ti modified coating.

[0050] Turn off the bias switch and DC power switch, turn off the target baffle, turn off the suspension frame self-rotation switch, and wait for the sample to cool to room temperature in the coating chamber to obtain boron fiber precursor filament.

[0051] Figure 1 This is a schematic diagram of magnetron sputtering of the boron fiber precursor filament of the present invention.

[0052] This invention does not specifically limit the arrangement method; it can be set according to the requirements of mechanical properties. In a specific embodiment of this invention, the arrangement method is preferably fiber bundles.

[0053] In this invention, the temperature of the hot isostatic pressing is preferably 450-750°C, more preferably 500-700°C, even more preferably 550-600°C, the pressure is preferably 50-200 MPa, more preferably 100-150 MPa, even more preferably 120 MPa, and the holding time is preferably 1-4 h, even more preferably 2-3 h.

[0054] In this invention, during the hot isostatic pressing process, the laid-up boron fiber precursor yarn is preferably placed into a sheath and then hot isostatic pressing is performed; the material of the sheath is preferably the same as the material of the outermost layer of the boron fiber precursor yarn. Specifically, in the embodiments of this application, the material of the sheath is preferably aluminum alloy.

[0055] Figure 2 This is a schematic diagram of the preparation method of the continuous boron fiber reinforced aluminum alloy matrix composite material of the present invention.

[0056] The following detailed description of the continuous boron fiber reinforced aluminum alloy matrix composite material and its preparation method provided by the present invention, with reference to the embodiments, should not be construed as limiting the scope of protection of the present invention.

[0057] Comparative Example 1

[0058] 1) Install a pair of 6061 aluminum alloy targets (150×75×6mm in size) onto the target position of the magnetron sputtering cathode, adjust the surfaces of the target materials to be parallel to each other, and set the target spacing to 22cm.

[0059] 2) Arrange the tungsten-core boron fiber monofilaments (100μm in diameter and 17mm in length) neatly on the sample holder with a fiber surface spacing of 0.5mm and place them on the hanging rack.

[0060] 3) Vacuuming is performed to reduce the vacuum level of the coating chamber to below 5×10⁻⁶. -4 Pa.

[0061] 4) Turn on the suspension bracket to rotate, and set the rotation speed to 5 r / min.

[0062] 5) Introduce argon gas, set the gas flow rate to 60 sccm, and adjust the gas pressure in the coating chamber to 0.3 Pa.

[0063] 6) Turn on the ion source, with a current of 0.3A and a voltage of 800V, and clean the tungsten core boron fiber monofilament for 30 minutes.

[0064] 7) After cleaning, adjust the argon flow rate and gate valve, adjust the gas pressure to 0.8Pa, and set the bias voltage to -100V.

[0065] 8) The DC power supply parameters for the 6061 aluminum alloy target were adjusted to a current of 2.0A, a voltage of 370V, and a sputtering time of 5 hours, resulting in an aluminum alloy coating thickness of 27μm, thus producing B. f / Al alloy precursor wire.

[0066] 9) Obtain B f Lightweight and high-strength Al alloy precursor wires are obtained through fiber bundle laying and hot isostatic pressing. f / Al-based composite material, hot isostatic pressing parameters were set as follows: temperature 600℃, pressure 120MPa, holding time 2h; according to Figure 2 The fiber bundles are laid out in the manner shown.

[0067] Comparative Example 2

[0068] 1) Tungsten-core boron fiber monofilaments (100 μm in diameter and 17 mm in length) were placed in a chemical vapor deposition apparatus. Methane, boron trichloride and hydrogen (volume ratio of methane, boron trichloride and hydrogen is 3:4:2) were introduced into the reaction chamber to atmospheric pressure. Then the temperature was raised to 1100℃ to produce a cracking reaction, and tungsten-core boron fiber monofilaments with a 1.5 μm B4C coating were obtained.

[0069] 2) Install a pair of 6061 aluminum alloy targets (150×75×6mm in size) onto the target position of the magnetron sputtering cathode, adjust the surfaces of the target materials to be parallel to each other, and set the target spacing to 22cm.

[0070] 3) Arrange the tungsten core boron fiber monofilaments with B4C coating neatly on the sample rack with a fiber surface spacing of 0.5 mm and place them on the hanging rack.

[0071] 4) Vacuuming is performed to reduce the vacuum level of the coating chamber to below 5 × 10⁻⁶. -4 Pa.

[0072] 5) Turn on the suspension bracket to rotate, and set the rotation speed to 5 r / min.

[0073] 6) Introduce argon gas, set the gas flow rate to 60 sccm, and adjust the gas pressure in the coating chamber to 0.3 Pa.

[0074] 7) Turn on the ion source, with a current of 0.3A and a voltage of 800V, and clean for 30 minutes.

[0075] 8) After cleaning, adjust the argon flow rate and gate valve, adjust the gas pressure to 0.8Pa, and set the bias voltage to -100V.

[0076] 9) The DC power supply parameters for the 6061 aluminum alloy target were adjusted to a current of 2.0A and a voltage of 370V. Sputtering was performed for 5 hours, resulting in an aluminum alloy coating thickness of 27μm, thus producing B. f / B4C / Al alloy precursor wire.

[0077] 10) Obtain B f Lightweight, high-strength B4C / Al alloy precursor wire is obtained through fiber bundle laying and hot isostatic pressing. f The B4C / Al-based composite material was subjected to the following hot isostatic pressing (HIP) parameters: temperature 600℃, pressure 120MPa, and holding time 2h; the fiber bundle arrangement was the same as that of Comparative Example 1.

[0078] Example 1

[0079] 1) Tungsten-core boron fiber monofilaments (100 μm in diameter and 17 mm in length) were placed in a chemical vapor deposition apparatus. Methane, boron trichloride and hydrogen (volume ratio of methane, boron trichloride and hydrogen is 3:4:2) were introduced into the reaction chamber to atmospheric pressure. Then the temperature was raised to 1100℃ to produce a cracking reaction, and tungsten-core boron fiber monofilaments with a 1.5 μm B4C coating were obtained.

[0080] 2) Install a pair of titanium metal targets (150×75×6mm in size) onto the target magnetron sputtering cathode position, and install a pair of 6061 aluminum alloy targets (150×75×6mm in size) onto the target magnetron sputtering cathode position. Adjust the surfaces of the target materials to be parallel to each other, and set the target spacing to 22cm.

[0081] 3) Arrange the tungsten core boron fiber monofilaments with B4C coating neatly on the sample rack with a fiber surface spacing of 0.5 mm and place them on the hanging rack.

[0082] 4) Vacuuming is performed to reduce the vacuum level of the coating chamber to below 5 × 10⁻⁶. -4 Pa.

[0083] 5) Turn on the suspension bracket to rotate, and set the rotation speed to 5 r / min.

[0084] 6) Introduce argon gas, set the gas flow rate to 60 sccm, and adjust the gas pressure in the coating chamber to 0.3 Pa.

[0085] 7) Turn on the ion source, with a current of 0.3A and a voltage of 800V, and clean the boron fiber monofilament with B4C coating for 30 minutes.

[0086] 8) After cleaning, adjust the argon flow rate and gate valve, adjust the gas pressure to 0.8Pa, and set the bias voltage to -100V; adjust the DC power supply parameters of the titanium metal target to 0.34A current, 350V voltage, and 30 minutes sputtering time, and the thickness of the obtained Ti coating is 500nm.

[0087] 9) The DC power supply parameters for the 6061 aluminum alloy target were adjusted as follows: current 2.0A, voltage 370V, sputtering time 5 hours, and Al alloy coating thickness 27μm. This resulted in the formation of B... f / B4C / Ti / Al alloy precursor wire.

[0088] 10) Obtain B f Lightweight, high-strength B4C / Ti / Al alloy precursor wire is obtained through fiber bundle laying and hot isostatic pressing. f The B4C / Ti / Al-based composite material was prepared with the following hot isostatic pressing parameters: temperature 600℃, pressure 120MPa, and holding time 2h; the fiber bundle arrangement was the same as that of Comparative Example 1.

[0089] Figure 3 B obtained from Comparative Example 1 f / Al alloy precursor wire (a), B obtained from Comparative Example 2 f / B4C / Al alloy precursor wire (b) and B obtained in Example 1 f Cross-sectional SEM image of the / B4C / Ti / Al alloy precursor wire (c). From Figure 3 It can be seen that the precursor filaments of the three composite materials have regular and complete shapes, good bonding between the fibers and the matrix, and the thickness of the matrix coating meets expectations.

[0090] Figure 4 B obtained from Comparative Example 1 f SEM images of cross-sections of Al-based composite materials, from Figure 4 It can be seen that: B f In the Al-based composite material, the shape of the boron fiber is eroded, and the fiber and the matrix are well bonded with no obvious gaps or pores.

[0091] Figure 5 B obtained as a comparative example 2 f SEM images of cross-sections of / B4C / Al-based composite materials, from Figure 5 It can be seen that: B f In the B4C / Al-based composite material, the boron fibers are regularly shaped and intact, the B4C coating is not severely eroded, and the fibers are well bonded to the matrix without gaps or pores.

[0092] Figure 6 B obtained in Example 1 f SEM images of cross-sections of / B4C / Ti / Al-based composite materials, from Figure 6 It can be seen that: B f The B4C / Ti / Al-based composite material contains no gaps or pores, the boron fibers are regularly shaped and intact, the B4C coating is not severely eroded, and a thin reaction zone is formed between the coating and the matrix, which is in line with the expectation of introducing a strong interface.

[0093] The tensile strength of the aluminum alloy and the composite materials obtained in the examples and comparative examples were tested using the GB / T228 tensile testing method. Figure 7 B prepared for this invention f A schematic diagram of the tensile specimens and dimensions of the / B4C / Ti / Al-based composite material. Results are shown below. Figure 8 As shown.

[0094] Figure 8 The alloy is aluminum alloy, and the B obtained in Comparative Example 1 is... f / Al-based composite material, B obtained from Comparative Example 2 f / B4C / Al-based composite material and B obtained in Example 1 f A comparison of the room temperature tensile strength of / B4C / Ti / Al based composites, from... Figure 8 It can be seen that the tensile strength of the aluminum-based composite material constructed with continuous boron fibers is significantly improved compared to aluminum alloys. Comparative Example 2 shows that B... f The B4C / Al-based composite material, due to the introduction of a B4C coating, protects the integrity of the boron fibers and improves tensile strength. Example 1 shows the B4C / Al-based composite material. f The B4C / Ti / Al-based composite material introduces a B4C / Ti double coating, which protects the integrity of the boron fibers while constructing a strong reaction interface, resulting in the best tensile strength.

[0095] The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A method for producing a continuous boron fiber-reinforced aluminum alloy matrix composite material, characterized by, The continuous boron fiber reinforced aluminum alloy matrix composite material is prepared by laying and hot isostatic pressing of boron fiber precursor filaments; the boron fiber precursor filaments comprise boron fiber filaments, a B4C layer, a Ti layer and an aluminum alloy layer deposited on the boron fiber filaments in sequence; the diameter of the boron fiber filaments is 85-125 μm, and the length is 15-20 mm; the thickness of the B4C layer is 1-4 μm; the thickness of the Ti layer is 300-800 nm, and the thickness of the aluminum alloy layer is 15-40 μm; comprising the following steps: depositing a B4C layer, a Ti layer and an aluminum alloy layer on the boron fiber filaments in sequence by chemical vapor deposition to obtain boron fiber precursor filaments; laying and hot isostatic pressing of the boron fiber precursor filaments to obtain the continuous boron fiber reinforced aluminum alloy matrix composite material.

2. The production method according to claim 1, characterized by, The deposition parameters of the B4C layer comprise: the working gas is methane, boron trichloride and hydrogen, the volume of the methane, boron trichloride and hydrogen is 2:1:1-2:6:5, the temperature of direct current heating cracking is 800-1400 ℃, and the reaction chamber pressure is atmospheric pressure.

3. The preparation method according to claim 1, characterized in that, The deposition parameters of the Ti layer comprise: the cathode target position is a Ti metal target, the protective gas is argon, the cavity gas pressure is 0.5-1.3 Pa, the bias voltage is -50--200 V, the current is 0.2-0.8 A, the voltage is 100-500 V, and the sputtering time is 6-60 min.

4. The method of claim 1, wherein, The deposition parameters of the aluminum alloy layer comprise: the cathode target position is an aluminum alloy target, the protective gas is argon, the cavity gas pressure is 0.5-1.3 Pa, the bias voltage is -50--200 V, the current is 1.0-3.0 A, the voltage is 100-500 V, the deposition rate is 3.0-10.0 μm / h, and the sputtering time is 3-6 h.

5. The preparation method according to claim 1, characterized in that, The temperature of the hot isostatic pressing is 450-750 ℃, the pressure is 50-200 MPa, and the pressure maintaining time is 1-4 h.

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