A super hybrid fiber reinforced metal laminate and its preparation method

Abstract

This invention discloses a super-hybrid fiber-reinforced metal laminate and its preparation method. The laminate comprises a titanium alloy plate, carbon fiber reinforced composite material, and foamed titanium composite material. In the layup of the laminate, the number of titanium alloy plates is X, the number of carbon fiber reinforced composite materials is Y, and the number of foamed titanium composite materials is Z, where X≥2, Y≥1, and Z≥1. Each layer of the same material is separated by at least one other material, and the outermost layer is a titanium alloy plate. The application of open-cell foamed titanium improves the strength and ablation resistance of the lightweight laminate. Titanium alloy, as the substrate, has a higher density and strength than aluminum alloy and does not undergo electrochemical corrosion with carbon fiber. Plasma treatment of the titanium alloy surface effectively solves the problem of adhesion to the composite material and enhances the interfacial bonding force.

Description

Technical Field

[0001] This invention relates to the field of aerospace materials technology, specifically to a super-hybrid fiber-reinforced metal laminate and its preparation method. Background Technology

[0002] Fiber metal laminates (FMLs) originated in the aerospace industry. They are hybrid composite materials formed by alternating layers of thin metal sheets and fiber composite materials, cured under specific temperature and pressure conditions; they are also known as super hybrid laminates. FMLs combine the performance characteristics of traditional fiber composite materials and metal materials, possessing not only the ductility and machinability of metals but also high fracture toughness, excellent impact resistance, fatigue resistance, flame retardancy, and lightning protection. With the continuous promotion of composite materials and the increasing demands for lightweight structures and integrated structural functions, their significant advantages have led to a year-on-year growth trend in the aerospace field.

[0003] The first generation of fiber-reinforced metal laminates, known as ARRAL, consisted of aramid fibers (Kevlar-49) and aluminum alloy. Initially designed for aircraft wings, it suffered from significant differences in thermal expansion coefficients between aramid fibers and aluminum alloys. This resulted in high residual stress during the curing and cooling process, which was difficult to adjust. Furthermore, the low fracture strain of aramid fibers led to poor formability, limiting its application to flat structures or components with small curvatures. In 1987, the second generation of glass fiber reinforced aluminum alloy laminates—GLARE—was introduced. GLARE boasted extremely high fatigue strength (more than three times that of 2024 aluminum) and damage tolerance (one to two times that of 2024 aluminum), high impact resistance (Glare 5-2 / 1-0.4 is nearly 86% higher than 2024-T3 of the same thickness), and significant weight reduction potential (15-30% weight reduction compared to 2024 aluminum). It became a major focus for the large-scale aerospace manufacturing industry, playing a crucial role in reducing the weight of large aircraft and improving their long-term lifespan and safety. The third-generation laminate is primarily the carbon fiber reinforced aluminum alloy laminate, CARALL. However, due to the potential difference between carbon fiber and aluminum alloy, electrochemical corrosion of the laminate is likely to occur. Currently, surface treatments such as coatings or fiber layers like glass fiber laid on both sides of the carbon fiber resin matrix composite are often used to isolate direct contact with the aluminum plate. However, it's difficult to completely avoid contact due to factors like sample cutting or laminate damage during service, and it also increases process complexity. The fourth-generation laminate is the graphite-reinforced titanium alloy laminate—TiGr. Titanium alloy has a higher density than aluminum alloy and does not exhibit electrochemical corrosion with graphite fibers. Furthermore, graphite fibers possess higher strength, specific modulus, high damage tolerance, and significant high-temperature performance. This type of laminate has superior mechanical properties and high-temperature resistance and is currently used in the leading edge and fuselage skin of the B787 and the engine doors of the V-22 helicopter. However, the high cost of titanium alloy and graphite fibers, coupled with the high fabrication temperature, makes its manufacturing cost far higher than that of Glare laminates.

[0004] Titanium is highly chemically reactive and readily reacts with elements such as oxygen and nitrogen at room temperature to form a dense, inert oxide film on its surface. In addition, the presence of grease on the surface of titanium alloys is almost unavoidable. Therefore, the bonding performance between titanium metal plates and fiber composite materials is greatly affected by the process, often resulting in unsatisfactory interfacial strength.

[0005] Hypersonic vehicles currently possess significant economic value in both national defense and civilian applications due to their high penetration success rate. When hypersonic vehicles fly at high speeds, the friction between the vehicle surface and the air generates a large amount of heat, causing the surface temperature to rise rapidly. For example, when cruise missiles fly at speeds of 680 m / s to 1020 m / s, the surface temperature of the missile body and wing skin can reach 200°C to 300°C, placing higher demands on hypersonic missile systems (FMLs). Conventional high-strength aluminum alloys (such as 2219 and 7050) and thermosetting epoxy resin-based composite materials cannot meet these requirements, and the curing process requires heat and pressure treatment, severely limiting production efficiency.

[0006] In summary, traditional fiber-metal laminates: (1) mostly use thermosetting epoxy resin as the resin matrix, which cannot be used for long-term service at high temperatures, has low ablation protection capability, and the curing process requires heat preservation and pressure preservation of the material, which restricts production efficiency; (2) graphite fiber is expensive and has high preparation cost; (3) aluminum alloy as metal substrate has potential corrosion with carbon fiber, and the aging behavior that occurs at high temperature will also seriously reduce its fracture toughness and fatigue performance; (4) the bonding performance between titanium alloy laminate and fiber composite material is greatly affected by the process.

[0007] Therefore, further improvements are needed for fiber-reinforced metal laminates. Summary of the Invention

[0008] The technical problem to be solved by the present invention is to propose a super hybrid fiber reinforced metal laminate with dual functions of ablation protection and high-speed impact resistance, in light of the above-mentioned technical status.

[0009] The second technical problem to be solved by the present invention is to provide a method for preparing the above-mentioned ultrahybrid fiber reinforced metal laminate.

[0010] The technical solution adopted by the present invention to solve the first technical problem is: a super hybrid fiber reinforced metal laminate, characterized in that the laminate includes a titanium alloy plate, a carbon fiber reinforced composite material and a foamed titanium composite material, wherein the number of titanium alloy plates in the laminate is X, the number of carbon fiber reinforced composite materials is Y, and the number of foamed titanium composite materials is Z, X≥2, Y≥1, Z≥1, and at least one other material is laid between the same materials, and the outermost layer is a titanium alloy plate.

[0011] Preferably, the carbon fiber reinforced composite material is composed of carbon fiber and phenolic resin, and the foamed titanium composite material is composed of foamed titanium and phenolic resin. Phenolic resin ensures the laminate can operate for extended periods at high temperatures, provides strong ablation protection, and offers higher production efficiency.

[0012] Preferably, the laminated sheet is laid up with titanium alloy plate, carbon fiber reinforced composite material, foamed titanium composite material, carbon fiber reinforced composite material, and titanium alloy plate.

[0013] Preferably, the laminated sheet is laid up with titanium alloy plate, foamed titanium composite material, carbon fiber reinforced composite material, foamed titanium composite material, and titanium alloy plate.

[0014] Preferably, the laminated sheet is laid up in the form of titanium alloy plate, foamed titanium composite material, carbon fiber reinforced composite material, titanium alloy plate, carbon fiber reinforced composite material, foamed titanium composite material, and titanium alloy plate.

[0015] Preferably, the laminated sheet is laid up in the form of titanium alloy plate, foamed titanium composite material, carbon fiber reinforced composite material, foamed titanium composite material, carbon fiber reinforced composite material, foamed titanium composite material, and titanium alloy plate.

[0016] The technical solution adopted by the present invention to solve the first technical problem is: a method for preparing a super-hybrid fiber reinforced metal laminate, characterized in that the method for preparing the above-mentioned super-hybrid fiber reinforced metal laminate includes the following steps:

[0017] Step 1, Preparation of carbon fiber reinforced composite material: Using compression molding process, carbon fiber and resin are mixed and loaded into a flat mold, flattened and pre-compacted, placed on a press and pressurized for step temperature curing, and finally demolded and cleaned to obtain carbon fiber reinforced composite material.

[0018] Step 2: Surface treatment of titanium alloy plate: The cleaned titanium alloy plate is subjected to plasma treatment on a plasma surface treatment device, and then the surface of the treated titanium alloy plate is treated with resin protection.

[0019] Step 3: Preparation of foamed titanium composite material: Titanium powder and pore-forming agent are mixed evenly, and then placed in an SPS sintering equipment for pressure sintering. The pore-forming agent is then cleaned off to obtain foamed titanium material. Finally, the foamed titanium composite material is obtained through RTM injection molding.

[0020] Step 4: Lay the laminates according to different layup design requirements and use an autoclave to form the laminated board in one step.

[0021] Preferably, in step one, the pressure curing method involves placing the premixed material into a flat mold treated with a preheated release agent, spreading and pre-compacting it, and then placing it on a 50T press for contact pressure and controlled heating. The pressure is increased to 5MPa according to the gel state, and the material is cured in stages at 90℃ / 1h, 120℃ / 1h, 160℃ / 1h, and 180℃ / 2h. Finally, the material is demolded and cleaned to obtain a carbon fiber reinforced phenolic resin matrix composite material.

[0022] Preferably, the plasma treatment process for titanium alloy in step two has the following process parameters: the treatment power is 800W, the treatment environment is air, the distance between the plasma gun and the surface of the test piece is 100mm, the treatment rate is 5m / min, the plasma treatment is performed twice, and the surface of the titanium plate is treated with resin after the plasma treatment.

[0023] Preferably, all resins used in the preparation method are high-carbon-residue phenolic resins. Using thermoplastic high-carbon-residue phenolic resins instead of the thermosetting epoxy resins used in traditional FMLs provides a more efficient ablation heat-resistant material due to its higher thermal decomposition temperature and high-temperature carbon residue rate. This allows for faster preparation and molding, significantly improving the efficiency of layer fabrication and reducing production costs. Furthermore, under the action of high-speed gas, the carbon-phenolic material undergoes phenolic resin decomposition and carbonization, and the heat generated by the high-speed airflow is absorbed by the decomposition of the phenolic resin, resulting in a significant heat-resistant effect.

[0024] Compared with the prior art, the advantages of the present invention are as follows:

[0025] (1) The introduction of open-cell foamed titanium can increase the strength of the laminate while maintaining its lightweight nature, and can also dissipate oxygen during the ablation process to improve the ablation resistance of the laminate.

[0026] (2) Titanium alloy is selected as the substrate. Titanium alloy has a higher density and strength than aluminum alloy, and there is no electrochemical corrosion between it and carbon fiber.

[0027] (3) Plasma treatment is performed on the surface of titanium alloy to solve the bonding problem between titanium plate and composite material, and greatly improve the interfacial strength between titanium plate and composite material.

[0028] (4) Carbon fiber replaces expensive and costly graphite fiber. Moreover, the heat generated by the high-speed airflow will cause the carbonized layer to transform into graphite, and at the same time trigger the sublimation heat of some carbon molecules. This process can absorb a lot of heat to achieve the purpose of heat protection. Attached Figure Description

[0029] Figure 1 This is a diagram illustrating the laminate laying and curing process according to an embodiment of the present invention;

[0030] Figure 2 This is a schematic diagram of the laminate laying sequence in Embodiment 1 of the present invention;

[0031] Figure 3 These are laminated boards with different laying sequences prepared according to the present invention. Detailed Implementation

[0032] The present invention will be further described in detail below with reference to the accompanying drawings and embodiments.

[0033] Example 1

[0034] (1) Preparation of carbon fiber reinforced phenolic resin

[0035] Carbon-phenolic heat-resistant material is prepared using a typical compression molding process. Carbon fibers are cut into 6mm short carbon fibers, which are then mixed with phenolic resin to obtain a short-cut molded carbon / phenolic premix. Next, the premix is ​​loosened, dispersed, and spread out, then air-dried at room temperature until it is no longer sticky. After preheating, it is evenly filled into a flat mold treated with a release agent, flattened, and pre-compacted. It is then placed on a 50T press for controlled heating under contact pressure, with pressure increased by 5MPa according to the gelation state. The material is cured in stages at 90℃ / 1h, 120℃ / 1h, 160℃ / 1h, and 180℃ / 2h. Finally, the mold is removed and cleaned to obtain a carbon fiber reinforced phenolic resin-based composite material.

[0036] (2) Surface treatment of titanium alloy plates

[0037] The titanium alloy sheet was ultrasonically cleaned with acetone for 20 minutes, followed by plasma treatment. The plasma treatment was performed on a TFR02-PL-3700 plasma surface treatment equipment with the following parameters: treatment power of 800W, treatment environment of air, plasma gun distance from the test piece surface of 100mm, treatment rate of 5m / min, and two plasma treatments. After plasma treatment, a resin protective treatment of approximately 0.02mm was applied to the titanium sheet surface to protect the activated surface and prevent oxidation of the titanium alloy sheet.

[0038] (3) Preparation of titanium foam

[0039] Titanium powder and NaCl pore-forming agent were mixed evenly in a powder mixer, and then ball-milled to ensure thorough mixing of the pore-forming agent and titanium powder. Hard alloy balls were used as the milling medium, with a ball-to-powder ratio of 10:1, a milling time of 30 hours, and a rotation speed of 400 r / min. Then, according to the mold size, the mixed powder was loaded into a graphite mold in an SPS sintering equipment and sintered under pressure. The sintered sample was repeatedly dissolved and washed in distilled water to remove the NaCl pore-forming agent, thus obtaining foamed titanium material. First, the foamed titanium was cut according to the mold size. The required injection mass of phenolic resin was calculated based on its volume fraction and mold size, and then vacuum-injected into the mold and sealed. The temperature was gradually increased to 180℃ in an oven and held for 4 hours to cure. The sample was then demolded and cleaned to obtain a resin-based ablation heat-resistant composite material based on a three-dimensional open-cell titanium foam skeleton reinforcement structure. The mechanical property parameters of this material are detailed in Table 1.

[0040] (4) Laminated boards

[0041] The manufacturing process references the Glare process for general-purpose laminated sheets used in aerospace applications. It employs a one-time molding process in an autoclave. After laying out the layers according to the design (TA1 / CFRP / Foam-Ti / CFRP / TA1), the curing process is carried out according to the following steps: First, a vacuum is drawn down to -950 mbar. Then, external pressure is applied. When the pressure rises to 6 bar, the vacuum inside the vacuum bag is raised to -100 mbar. The system is heated to 60°C at a rate of 1.5°C / min, then to 177°C at a rate of 0.75°C / min, and held at that temperature for 4 hours. Finally, the temperature is lowered to 80°C at a rate of 0.75°C / min, and then to room temperature at a rate of 1.5°C / min, thus obtaining the carbon fiber reinforced titanium alloy laminated sheet.

[0042] This embodiment employs thermoplastic high-carbon-residue phenolic resin as a novel ablation heat-resistant material to replace the thermosetting epoxy resin used in traditional FMLs. High-carbon-residue phenolic resin is renowned for its superior thermal stability; its thermal decomposition temperature is significantly higher than that of epoxy resin, and it exhibits a higher carbon residue at high temperatures. This means it can more effectively maintain structural integrity under extreme conditions. Therefore, as an advanced ablation material, high-carbon-residue phenolic resin can provide more reliable protection in extreme environments.

[0043] The laminate prepared in this embodiment underwent a comprehensive evaluation of its mechanical properties through experiments, and the relevant data are detailed in Table 1. The results show that, compared with traditional materials, the newly prepared laminate exhibits superior performance in terms of tensile strength, flexural modulus, and flexural strength. These improved mechanical properties endow the laminate with stronger resistance to high-speed impacts, making it more advantageous for applications in the aerospace field.

[0044] Table 1 Mechanical properties of the titanium foam and laminate prepared in Example 1

[0045] foamed titanium 32 2 56 Example 1: Laminated Board 182 2 177

[0046] Example 2

[0047] (1) Preparation of carbon fiber reinforced phenolic resin

[0048] Carbon-phenolic heat-resistant material is prepared using a typical compression molding process. Carbon fibers are cut into 6mm short carbon fibers, which are then mixed with phenolic resin to obtain a short-cut molded carbon / phenolic premix. Next, the premix is ​​loosened, dispersed, and spread out, then air-dried at room temperature until it is no longer sticky. After preheating, it is evenly filled into a flat mold treated with a release agent, flattened, and pre-compacted. It is then placed on a 50T press for controlled heating under contact pressure, with pressure increased by 5MPa according to the gelation state. The material is cured in stages at 90℃ / 1h, 120℃ / 1h, 160℃ / 1h, and 180℃ / 2h. Finally, the mold is removed and cleaned to obtain a carbon fiber reinforced phenolic resin-based composite material.

[0049] (2) Surface treatment of titanium alloy plates

[0050] The titanium alloy sheet was ultrasonically cleaned with acetone for 20 minutes, followed by plasma treatment. The plasma treatment was performed on a TFR02-PL-3700 plasma surface treatment equipment with the following parameters: treatment power of 800W, treatment environment of air, plasma gun distance from the test piece surface of 100mm, treatment rate of 5m / min, and two plasma treatments. After plasma treatment, a resin protective treatment of approximately 0.02mm was applied to the titanium sheet surface to protect the activated surface and prevent oxidation of the titanium alloy sheet.

[0051] (3) Preparation of titanium foam

[0052] Titanium powder and NaCl pore-forming agent were mixed evenly in a powder mixer, and then ball-milled to ensure thorough mixing of the pore-forming agent and titanium powder. Hard alloy balls were used as the milling medium, with a ball-to-powder ratio of 10:1, a milling time of 30 hours, and a rotation speed of 400 r / min. Then, according to the mold size, the mixed powder was loaded into a graphite mold in an SPS sintering equipment and sintered under pressure. The sintered sample was repeatedly dissolved and washed in distilled water to remove the NaCl pore-forming agent, thus obtaining foamed titanium material. First, the foamed titanium was cut according to the mold size. The required injection mass of phenolic resin was calculated based on its volume fraction and mold size, and then vacuum-injected into the mold and sealed. The temperature was gradually increased to 180℃ in an oven and held for 4 hours to cure. The sample was then demolded and cleaned, yielding a resin-based ablation heat-resistant composite material with a three-dimensional open-cell titanium foam skeleton reinforcement structure.

[0053] (4) Laminated boards

[0054] The manufacturing process references the Glare process for general-purpose laminated sheets used in aerospace applications. It involves one-time molding in an autoclave. After laying out the layers according to the design (TA1 / Foam-Ti / CFRP / Foam-Ti / TA1), the following curing steps are followed: First, a vacuum is drawn down to -950 mbar. Then, external pressure is applied. When the pressure rises to 6 bar, the vacuum inside the vacuum bag is raised to -100 mbar. The system is heated to 60°C at a rate of 1.5°C / min, then to 177°C at a rate of 0.75°C / min, and held at that temperature for 4 hours. Finally, the temperature is lowered to 80°C at a rate of 0.75°C / min, and then to room temperature at a rate of 1.5°C / min, thus obtaining the carbon fiber reinforced titanium alloy laminated sheet.

[0055] Example 3

[0056] (1) Preparation of carbon fiber reinforced phenolic resin

[0057] Carbon-phenolic heat-resistant material is prepared using a typical compression molding process. Carbon fibers are cut into 6mm short carbon fibers, which are then mixed with phenolic resin to obtain a short-cut molded carbon / phenolic premix. Next, the premix is ​​loosened, dispersed, and spread out, then air-dried at room temperature until it is no longer sticky. After preheating, it is evenly filled into a flat mold treated with a release agent, flattened, and pre-compacted. It is then placed on a 50T press for controlled heating under contact pressure, with pressure increased by 5MPa according to the gelation state. The material is cured in stages at 90℃ / 1h, 120℃ / 1h, 160℃ / 1h, and 180℃ / 2h. Finally, the mold is removed and cleaned to obtain a carbon fiber reinforced phenolic resin-based composite material.

[0058] (2) Surface treatment of titanium alloy plates

[0059] The titanium alloy sheet was ultrasonically cleaned with acetone for 20 minutes, followed by plasma treatment. The plasma treatment was performed on a TFR02-PL-3700 plasma surface treatment equipment with the following parameters: treatment power of 800W, treatment environment of air, plasma gun distance from the test piece surface of 100mm, treatment rate of 5m / min, and two plasma treatments. After plasma treatment, a resin protective treatment of approximately 0.02mm was applied to the titanium sheet surface to protect the activated surface and prevent oxidation of the titanium alloy sheet.

[0060] (3) Preparation of titanium foam

[0061] Titanium powder and NaCl pore-forming agent were mixed evenly in a powder mixer, and then ball-milled to ensure thorough mixing of the pore-forming agent and titanium powder. Hard alloy balls were used as the milling medium, with a ball-to-powder ratio of 10:1, a milling time of 30 hours, and a rotation speed of 400 r / min. Then, according to the mold size, the mixed powder was loaded into a graphite mold in an SPS sintering equipment and sintered under pressure. The sintered sample was repeatedly dissolved and washed in distilled water to remove the NaCl pore-forming agent, thus obtaining foamed titanium material. First, the foamed titanium was cut according to the mold size. The required injection mass of phenolic resin was calculated based on its volume fraction and mold size, and then vacuum-injected into the mold and sealed. The temperature was gradually increased to 180℃ in an oven and held for 4 hours to cure. The sample was then demolded and cleaned, yielding a resin-based ablation heat-resistant composite material with a three-dimensional open-cell titanium foam skeleton reinforcement structure.

[0062] (4) Laminated boards

[0063] The manufacturing process references the Glare process for general-purpose laminated sheets used in aerospace applications. It employs a one-time molding process in an autoclave. After laying out the layers according to the design (TA1 / Foam-Ti / CFRP / TA1 / CFRP / Foam-Ti / TA1), the following curing steps are followed: First, a vacuum is drawn down to -950 mbar. Then, external pressure is applied. When the pressure rises to 6 bar, the vacuum inside the vacuum bag is raised to -100 mbar. The system is heated to 60°C at a rate of 1.5°C / min, then to 177°C at a rate of 0.75°C / min, and held at that temperature for 4 hours. Finally, the temperature is lowered to 80°C at a rate of 0.75°C / min, and then to room temperature at a rate of 1.5°C / min, thus obtaining the carbon fiber reinforced titanium alloy laminated sheet.

[0064] Example 4

[0065] (1) Preparation of carbon fiber reinforced phenolic resin

[0066] Carbon-phenolic heat-resistant material is prepared using a typical compression molding process. Carbon fibers are cut into 6mm short carbon fibers, which are then mixed with phenolic resin to obtain a short-cut molded carbon / phenolic premix. Next, the premix is ​​loosened, dispersed, and spread out, then air-dried at room temperature until it is no longer sticky. After preheating, it is evenly filled into a flat mold treated with a release agent, flattened, and pre-compacted. It is then placed on a 50T press for controlled heating under contact pressure, with pressure increased by 5MPa according to the gelation state. The material is cured in stages at 90℃ / 1h, 120℃ / 1h, 160℃ / 1h, and 180℃ / 2h. Finally, the mold is removed and cleaned to obtain a carbon fiber reinforced phenolic resin-based composite material.

[0067] (2) Surface treatment of titanium alloy plates

[0068] The titanium alloy sheet was ultrasonically cleaned with acetone for 20 minutes, followed by plasma treatment. The plasma treatment was performed on a TFR02-PL-3700 plasma surface treatment equipment with the following parameters: treatment power of 800W, treatment environment of air, plasma gun distance from the test piece surface of 100mm, treatment rate of 5m / min, and two plasma treatments. After plasma treatment, a resin protective treatment of approximately 0.02mm was applied to the titanium sheet surface to protect the activated surface and prevent oxidation of the titanium alloy sheet.

[0069] (3) Preparation of titanium foam

[0070] Titanium powder and NaCl pore-forming agent were mixed evenly in a powder mixer, and then ball-milled to ensure thorough mixing of the pore-forming agent and titanium powder. Hard alloy balls were used as the milling medium, with a ball-to-powder ratio of 10:1, a milling time of 30 hours, and a rotation speed of 400 r / min. Then, according to the mold size, the mixed powder was loaded into a graphite mold in an SPS sintering equipment and sintered under pressure. The sintered sample was repeatedly dissolved and washed in distilled water to remove the NaCl pore-forming agent, thus obtaining foamed titanium material. First, the foamed titanium was cut according to the mold size. The required injection mass of phenolic resin was calculated based on its volume fraction and mold size, and then vacuum-injected into the mold and sealed. The temperature was gradually increased to 180℃ in an oven and held for 4 hours to cure. The sample was then demolded and cleaned, yielding a resin-based ablation heat-resistant composite material with a three-dimensional open-cell titanium foam skeleton reinforcement structure.

[0071] (4) Laminated boards

[0072] The manufacturing process references the Glare process for general-purpose laminated sheets used in aerospace applications. It employs a one-time molding process in an autoclave. After laying the sheets according to the layup design (TA1 / Foam-Ti / CFRP / Foam-Ti / CFRP / Foam-Ti / TA1), the curing process is carried out according to the following steps: First, a vacuum is drawn down to -950 mbar. Then, external pressure is applied. When the pressure rises to 6 bar, the vacuum inside the vacuum bag is raised to -100 mbar. The system is heated to 60°C at a rate of 1.5°C / min, then to 177°C at a rate of 0.75°C / min, and held at that temperature for 4 hours. Finally, the temperature is lowered to 80°C at a rate of 0.75°C / min, and then to room temperature at a rate of 1.5°C / min, thus obtaining the carbon fiber reinforced titanium alloy laminated sheet.

Claims

1. A super-hybrid fiber-reinforced metal laminate, characterized in that, The laminated sheet includes titanium alloy sheet, carbon fiber reinforced composite material and foamed titanium composite material. The number of titanium alloy sheets in the laminated sheet is X, the number of carbon fiber reinforced composite material is Y, and the number of foamed titanium composite material is Z, where X≥2, Y≥1, and Z≥1. There is at least one other material between the same materials, and the outermost layer is a titanium alloy sheet. The carbon fiber reinforced composite material is composed of carbon fiber and phenolic resin, and the foamed titanium composite material is composed of foamed titanium and phenolic resin. The foamed titanium composite material is obtained by RTM injection process, and the titanium alloy plate is subjected to plasma treatment.

2. The ultra-hybrid fiber-reinforced metal laminate according to claim 1, characterized in that, The laminated sheet is laid up with titanium alloy plate, carbon fiber reinforced composite material, foamed titanium composite material, carbon fiber reinforced composite material, and titanium alloy plate.

3. The ultra-hybrid fiber-reinforced metal laminate according to claim 1, characterized in that, The laminated sheet is laid up with titanium alloy plate, foamed titanium composite material, carbon fiber reinforced composite material, foamed titanium composite material, and titanium alloy plate.

4. The ultra-hybrid fiber-reinforced metal laminate according to claim 1, characterized in that, The laminated sheet is laid up in the following order: titanium alloy plate, titanium foam composite material, carbon fiber reinforced composite material, titanium alloy plate, carbon fiber reinforced composite material, titanium foam composite material, and titanium alloy plate.

5. The ultra-hybrid fiber-reinforced metal laminate according to claim 1, characterized in that, The laminated sheet is laid up with titanium alloy plate, foamed titanium composite material, carbon fiber reinforced composite material, foamed titanium composite material, carbon fiber reinforced composite material, foamed titanium composite material, and titanium alloy plate.

6. A method for preparing a super-hybrid fiber-reinforced metal laminate, characterized in that, The preparation of the ultra-hybrid fiber-reinforced metal laminate according to any one of claims 1 to 5 includes the following steps: Step 1, Preparation of carbon fiber reinforced composite material: Using compression molding process, carbon fiber and resin are mixed and loaded into a flat mold, flattened and pre-compacted, placed on a press and pressurized for step temperature curing, and finally demolded and cleaned to obtain carbon fiber reinforced composite material. Step 2: Surface treatment of titanium alloy plate: The cleaned titanium alloy plate is subjected to plasma treatment on a plasma surface treatment device, and then the surface of the treated titanium alloy plate is treated with resin protection. Step 3: Preparation of foamed titanium composite material: Titanium powder and pore-forming agent are mixed evenly, and then loaded into SPS sintering equipment and sintered under pressure; then the pore-forming agent is cleaned to obtain foamed titanium material, and then foamed titanium composite material is obtained through RTM injection process; Step 4: Lay the laminates according to different layup design requirements and use an autoclave to form the laminated board in one step.

7. The preparation method according to claim 6, characterized in that, In step one, the pressure curing method involves placing the premixed material into a flat mold treated with a preheated release agent, spreading and pre-compacting it, and then placing it on a 50T press for contact pressure and controlled heating. The pressure is increased to 5MPa according to the gel state, and the material is cured in stages at 90℃ / 1h, 120℃ / 1h, 160℃ / 1h, and 180℃ / 2h. Finally, the mold is removed and cleaned to obtain a carbon fiber reinforced phenolic resin matrix composite material.

8. The preparation method according to claim 6 or 7, characterized in that, The plasma treatment process for titanium alloy in step two has the following parameters: the treatment power is 800W, the treatment environment is air, the distance between the plasma gun and the surface of the test piece is 100mm, the treatment rate is 5m / min, the plasma treatment is performed twice, and the surface of the titanium plate is treated with resin after the plasma treatment.

9. The preparation method according to claim 8, characterized in that, All resins used in the preparation method are high-carbon phenolic resins.

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