Preparation method of titanium-based composite material sheet with lamellar structure

Abstract

The invention relates to the technical field of titanium-based composite material sheet preparation, and particularly provides a preparation method of a titanium-based composite material sheet with a lamellar structure. The preparation method of the lamellar-structure titanium-based composite material thin plate comprises the following steps: S1, repeatedly remelting raw materials through vacuum self-consumption to obtain a particle-reinforced titanium-based composite material cast ingot; s2, the cast ingot is subjected to cogging forging, first-stage forging, second-stage forging and shaping forging, and a titanium-based composite material plate blank is obtained; s3, the titanium-based composite plate blank is subjected to rough rolling treatment and finish rolling treatment, and a sheet semi-finished product is obtained; and S4, carrying out surface treatment on the sheet semi-finished product to obtain the titanium-based composite material sheet with the lamellar structure. Through the slab forging process design and the sheet rolling process design, particle reinforced phase distribution, size and matrix structure are optimized, regulated and controlled, and good matching of processing formability, high-temperature heat resistance and heat stability of the titanium-based composite sheet is achieved.

Description

Technical Field

[0001] The invention relates to the technical field of titanium-based composite material plate preparation, and in particular to a method for preparing a titanium-based composite material thin plate with a lamellar structure. Background Art

[0002] In order to meet the requirements of processes such as superplastic forming, the current mainstream high-temperature titanium alloy thin plates generally adopt a fine-grained equiaxed structure design. Although it has good process plasticity and processing formability, its yield strength, endurance life and creep resistance are much lower than those of dual-state or lamellar structures because the deformation mechanism is dominated by grain boundary sliding at high temperatures. In addition, the thin plates have serious surface oxidation and deformation problems during high-temperature heating, making heat treatment modification difficult. On the other hand, the grain size of traditional high-temperature titanium alloys is sensitive to temperature. When heated or deformed in the β phase region, the grains are easily coarsened, resulting in difficulties in controlling the uniformity of organizational properties and making it difficult to meet the long-term high-temperature service requirements of the new generation of aerospace vehicles. Titanium-based composites can effectively hinder grain boundary migration and grain growth by introducing a ceramic reinforcement phase with high thermal stability (such as TiB) into the titanium alloy matrix, preventing excessive coarsening of the organization at high temperatures, and providing a theoretical possibility for the preparation of high-performance lamellar structure thin plates.

[0003] However, research on titanium-based composite thin plates in China is currently limited. The preparation processes often follow traditional high-temperature titanium alloy technology, focusing primarily on cracking during plate preparation and conventional room-temperature strength indicators. The microstructures of the resulting thin plates are still primarily equiaxed, equiaxed, and lamellar, similar to traditional high-temperature titanium alloys, failing to fully exploit the potential of the composite reinforcement phase in inhibiting grain growth and improving high-temperature performance. For example, patent CN111500957B discloses a method for preparing titanium-based composite plates resistant to 700°C. Plates with thicknesses of 1.8 to 4 mm were prepared by isothermal forging and rolling in the β / α+β phase region, but the creep resistance was not detailed, and the microstructure was not clearly defined as a lamellar structure. Patent CN117428003A discloses a cladding and rolling method for preparing large-scale titanium-based composite thin plates resistant to 750°C. The method focuses on the cladding and rolling process, with plate forming primarily occurring in the α+β phase region. The microstructure and properties of the final plate are unknown. Therefore, in response to the demand for lightweight heat-resistant metal sheet materials for the new generation of aerospace vehicles, it is urgent to develop a method that can effectively prepare heat-resistant titanium-based composite material sheets with a lamellar structure to solve the current problems of insufficient high-temperature yield strength, durability and creep resistance of conventional high-temperature titanium alloy sheets. Summary of the Invention

[0004] In response to the above problems, the present invention provides a method for preparing a lamellar structure titanium-based composite material sheet. Through specific forging and rolling process design, it effectively overcomes the difficulties of titanium-based composite materials such as high deformation resistance, easy cracking, and difficult control of reinforcement phase distribution, and obtains a lamellar structure titanium-based composite material sheet with ideal comprehensive performance matching.

[0005] In order to solve the above technical problems, in a first aspect, the present invention provides a method for preparing a lamellar structure titanium-based composite material sheet, comprising the following steps: S1. The raw materials are repeatedly remelted by vacuum consumable melting to obtain a particle-reinforced titanium-based composite ingot; S2. The ingot is forged into a slab to obtain a titanium-based composite material slab; the slab forging comprises: subjecting the ingot to open forging, performing 1 to 2 fires of open deformation at 1150-1200°C, with a total forging ratio of ≥6 for each fire, air cooling after forging, to obtain an open forged slab; subjecting the open forged slab to a primary forging process, heating it to T β ~T β +100℃ for 1~4 times of upsetting deformation, with the total forging ratio of each fire being greater than 8, and air cooling after forging to obtain a first-level forging billet; the first-level forging billet is subjected to secondary forging and heated to T β -40℃~T β +80℃ for 2~5 times of upsetting deformation, with the total forging ratio of each fire being greater than 6, and air cooling after forging to obtain a secondary forging billet; the secondary forging billet is subjected to shaping forging and heated to T β -30℃~T β The slab is deformed at +60℃ for 1~2 times with a final forging ratio of 1.2~2.0, and air-cooled after forging to obtain a titanium-based composite slab; S3 the titanium-based composite material slab by sheet rolling to obtain a sheet semi-finished product; the sheet rolling comprises: the titanium-based composite material slab rough rolling treatment, in T β -40℃~T β +50℃ for 1~4 times of rolling deformation, the holding time is H×(0.8~2.0)min, and the total deformation of the fire is ≥50%; the titanium-based composite material slab after rough rolling is welded and clad. β ~T β Finish rolling is performed at +100°C for a heating time of H×(0.8-1.5) min, and the coating material is removed after air cooling to obtain a thin semi-finished product; wherein H is the slab thickness in mm; the total number of rolling deformations in the rough rolling and finish rolling is 2-6 times; S4. Surface treatment is performed on the semi-finished thin plate to obtain the lamellar structure titanium-based composite material thin plate.

[0006] At present, particle reinforced titanium-based composite materials mainly use TiB, TiC and rare earth phase as reinforcement phase. In titanium-based composite materials prepared by melt casting, TiB reinforcement phase is usually in the form of whiskers with high aspect ratio. If the whiskers are not broken sufficiently during the forging stage, they will be inherited into the subsequent thin plates, resulting in poor plasticity of the tissue and easy to have obvious directionality, affecting the uniformity of the various directional properties of the plate. The present invention adopts a multi-stage forging process design, including blanking, primary, secondary and shaping forging. In the primary forging stage, the TiB reinforcement phase is formed in the T β ~T β Within a temperature range of +100°C, alternating axial and radial upsetting deformation is employed, coupled with a high forging ratio exceeding 8 per fire. This exerts intense multi-directional deformation forces, effectively breaking up the elongated TiB whiskers and significantly reducing their aspect ratio. Simultaneously, strict control of the temperature range, fire number, forging ratio, and deformation speed at each forging stage ensures sufficient deformation and breaking up of the reinforcing phases, while also reducing the risk of cracking in highly deformable materials during the forging process. This provides slabs with excellent microstructure uniformity for subsequent rolling.

[0007] Deformation in the β phase region is the key to obtaining a lamellar structure. This invention precisely controls the temperature window of rough rolling and finishing rolling, combined with a specific rolling deformation process design, to coordinately regulate the key organizational factors that determine the room temperature plasticity and high temperature thermal strength performance matching of the plate, such as β grain size, lamellar thickness, cluster size and orientation. β -40℃~T β At +50℃, by applying high total deformation, combining multi-pass deformation and reversing operation, high temperature tempering is used to promote dynamic recrystallization of β grains, refine grains and disperse cluster orientation. β ℃~T β Within the temperature range of +100°C, the deformation amount of each pass and the total number of fires are precisely controlled to achieve precise adjustment of the final sheet thickness and bundle size. Welding cladding is used before finishing rolling to effectively prevent high-temperature oxidation and temperature drop. At the same time, the rough rolling insulation and finishing rolling heating times are scientifically set according to the slab thickness to ensure that the slab is evenly heated in the target temperature range to achieve uniform deformation and phase change of the organization. The present invention precisely controls the rolling temperature, fire number, deformation amount of each fire, pass number, deformation amount of each pass, and reversing process to synergistically optimize the matrix organization and reinforcement phase distribution, effectively reducing the difference in transverse and longitudinal performance of the thin plate, improving the overall plasticity of the thin plate, and obtaining a lamellar structure heat-resistant titanium-based composite material sheet with good room temperature plasticity and excellent high-temperature strength, long-lasting life and creep resistance.

[0008] In the present invention, T β It is the phase transition temperature of titanium matrix composite material from α+β two-phase region to β phase.

[0009] Preferably, in step S1, the raw materials include zero-grade titanium sponge, high-purity aluminum beans, high-purity zirconium sponge, aluminum-silicon master alloy, aluminum-molybdenum master alloy, aluminum-niobium master alloy, high-purity yttrium powder or aluminum-yttrium master alloy, and titanium diboride powder.

[0010] Preferably, in step S2, the deformation speed of the blanking forging is 20~70mm / s, the deformation speed of the primary forging is 20~60mm / s, the deformation speed of the secondary forging is 10~50mm / s, and the deformation speed of the shaping forging is 10~40mm / s.

[0011] Preferably, in step S2, during the primary forging process, iron drawing is performed alternately along the axial and radial directions of the ingot.

[0012] Preferably, in step S3, in the rough rolling process, 2 to 8 deformation passes are performed in each fire, the deformation amount of each pass is 8% to 35%, and reversal is performed after each fire deformation.

[0013] Preferably, in step S3, the titanium-based composite material slab after the rough rolling treatment is first polished, pickled and cut into pieces before the finish rolling treatment, and the cutting size is determined according to the specifications of the finished plate.

[0014] Preferably, in step S3, in the finish rolling process, the number of rolling passes is 3 to 8, and the deformation amount per pass is controlled between 10% and 40%.

[0015] Preferably, in step S4, the surface treatment includes surface sanding treatment and acid-alkali cleaning treatment.

[0016] Preferably, the chemical composition of the lamellar structure titanium-based composite material sheet is as follows, calculated by weight percentage: Al: 6.2wt%~6.9wt%, Sn: 1.1wt%~3.5wt%, Zr: 2.3wt%~10.5wt%, Mo: 0.3wt%~2.3wt%, Nb: 0.7wt%~2.5wt%, Si: 0.2wt%~0.6wt%, O: 0.05wt%~0.15wt%, B: 0.12wt%~0.7wt%, Y: ≤0.3wt%, C: ≤0.1wt%, Fe: ≤0.035wt%, and the balance is Ti, among which the contents of Al, Sn, and Zr satisfy: (Al+Sn / 3+Zr / 6)≤8.8.

[0017] In a second aspect, the present invention provides a lamellar structure titanium-based composite material thin plate, which is prepared according to the above-mentioned method for preparing a lamellar structure titanium-based composite material thin plate.

[0018] Compared with the prior art, the present invention has the following beneficial effects: This paper, focusing on particle-reinforced heat-resistant titanium-based composite materials and based on the actual production conditions of large-scale thin plates, proposes a method for producing heat-resistant titanium-based composite sheets with a lamellar structure by direct rolling without heat treatment. Through the rational design of the slab forging and sheet rolling processes, the resulting heat-resistant titanium-based composite sheet achieves an ideal combination of room-temperature plasticity and high-temperature thermal strength.

[0019] Currently, the yield strength of conventional fine-grained, equiaxed high-temperature titanium alloy sheets at 650°C ranges from 200MPa to 400MPa, with a time to fracture at 650°C / 240MPa of less than 10 hours, a time to fracture at 600°C / 200MPa of less than 200 hours, and a creep residual strain of >1% at 650°C / 100MPa / 100h. The lamellar titanium-based composite sheet prepared by the present invention has a yield strength of >465MPa at 650°C, a time to fracture at 650°C / 240MPa of ≥30 hours, a time to fracture at 600°C / 200MPa of >300 hours, and a creep residual strain of <0.5% at 650°C / 100MPa / 100h. Compared to conventional equiaxed high-temperature titanium alloy sheets, the present sheet, under the same operating environment and with the same specifications, has a high-temperature yield strength increased by more than 20%, and creep resistance increased by more than three times. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 The 0.8 mm thick lamellar structure titanium-based composite material sheet structure (20 μm) in Example 1 of the present invention; Figure 2 This is the 1.2 mm thick lamellar structure titanium-based composite material sheet structure (20 μm) in Example 2 of the present invention. DETAILED DESCRIPTION

[0021] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the specific implementation methods will be briefly introduced below. Obviously, the embodiments described below are some implementation methods of the present invention. For ordinary technicians in this field, other implementation methods can be obtained based on these embodiments without paying creative work.

[0022] If specific experimental steps or conditions are not specified in the examples, the procedures or conditions of conventional experimental steps described in the literature in the field can be followed. All raw materials and instruments used are commercially available, including but not limited to those used in the examples of this application.

[0023] Example 1 This embodiment provides a lamellar structure titanium-based composite material thin plate, whose designed composition, calculated by weight percentage, is: Al: 6.48wt%, Sn: 1.97wt%, Zr: 4.06wt%, Mo: 0.46wt%, Nb: 1.79wt%, Si: 0.34wt%, B: 0.49wt%, and the balance is Ti, wherein the contents of Al, Sn, and Zr satisfy: (Al+Sn / 3+Zr / 6)≤8.8.

[0024] This embodiment provides a method for preparing the above-mentioned lamellar structure titanium-based composite material sheet, comprising the following steps: (1) Vacuum consumable arc melting: First, the ingredients are calculated according to the above alloy composition to determine the content of each element required for the preparation of 1000kg ingot. Then, the content of each raw material for smelting is determined based on the calculated element content, including zero-grade sponge titanium, high-purity aluminum beans, high-purity sponge zirconium, aluminum-silicon master alloy, aluminum-molybdenum master alloy, aluminum-niobium master alloy, and titanium diboride powder. A high-precision balance is used to weigh the calculated raw materials. Then, an automatic mixing system is used to uniformly mechanically mix the raw materials. The above uniformly mixed raw materials are pressed by a 6000T electrode press to obtain a consumable electrode. The pressed consumable electrode is combined and welded using a vacuum plasma welding box to obtain a combined billet. The combined billet is subjected to three vacuum consumable arc melting processes with a melting vacuum degree of ≤5Pa to obtain a particle-reinforced titanium-based composite ingot. After the ingot is subjected to riser, ingot bottom sawing and skinning treatment, a finished ingot of φ620mm is obtained.

[0025] (2) Slab forging: The ingot obtained in step (1) is subjected to one heat forging deformation at 1150°C using a fast forging machine. The ingot is heated by a step preheating method with a preheating temperature of ≥800°C. During the forging process, the ingot is wrapped with heat-insulating cotton. The total forging ratio of each fire is 7.2. The deformation speed is controlled at 20-70 mm / s. The final forging temperature is ≥950°C. After forging, the ingot is air-cooled to obtain a forged billet. After the forging is opened, the billet is heated to the preset temperature using a step heating method and then subjected to four rounds of upsetting and drawing deformation. The four fire temperatures are 1100℃, 1090℃, 1080℃ and 1070℃ respectively. The step preheating temperature is ≥800℃. During the forging process, insulation cotton is wrapped. The forging deformation speed is controlled at 20-60mm / s. The drawing process is carried out alternately along the axial and radial directions of the ingot. The total forging ratio of each fire is 8.5. The final forging temperature is ≥900℃. After forging, it is air-cooled to obtain the first-level forging billet. The first-level forging billet is reheated to 1000℃ and subjected to three rounds of upsetting and drawing deformation. The step preheating temperature is ≥800℃. During the forging process, insulation cotton is wrapped. The forging deformation speed is controlled at 10-50mm / s. The total forging ratio of each fire is 6.4. The final forging temperature is ≥850℃. After forging, it is air-cooled to obtain the second-level forging billet. The secondary forging blank is heated to 1050℃ for two rounds of slab forging and shaping. The forging deformation speed is controlled at 10~40mm / s. The forging ratio of the last round is 1.5. After forging, the blank is air-cooled to obtain a titanium-based composite material slab.

[0026] (3) Thin plate rolling: The titanium-based composite material slab obtained in step (2) is subjected to 4 rounds of rolling deformation. The rolling temperature of the first 3 rounds is 1060°C, and the holding time is determined by H×(0.8~2.0)min, where H is the total thickness of the slab, in mm. Each round is subjected to 6 rounds of deformation, with a deformation amount of 8%~35% per round and a total deformation amount of >50%. After each round of deformation, the direction is reversed and the cooling method is air cooling. After 3 rounds of rolling deformation, the slab is polished, pickled and cut into pieces. The cutting size is determined according to the specifications of the finished plate. The cut slab is welded and clad with metal plates. After cladding, thin plate rolling is carried out at a temperature of 1100°C. The heating time of the slab is determined by H×(0.8~1.5)min, the rolling passes are 5, and the deformation amount of each pass is controlled between 10%~40%. After air cooling, the cladding material is removed to obtain a thin plate semi-finished product.

[0027] (4) Surface treatment: The semi-finished thin plate obtained in step (3) was subjected to surface sanding and acid-alkali cleaning to obtain finished lamellar titanium-based composite material thin plates with thicknesses of 0.8 mm and 1.2 mm, respectively. The microstructure was examined using a metallographic microscope. Figure 1 shown.

[0028] Example 2 This embodiment provides a lamellar structure titanium-based composite material thin plate, whose designed composition, calculated by weight percentage, is: Al: 6.38wt%, Sn: 2.84wt%, Zr: 4.02wt%, Mo: 0.5wt%, Nb: 1.79wt%, Si: 0.36wt%, Y: 0.09wt%, B: 0.5wt%, and the balance is Ti, wherein the contents of Al, Sn, and Zr satisfy: (Al+Sn / 3+Zr / 6)≤8.8.

[0029] This embodiment provides a method for preparing the above-mentioned lamellar structure titanium-based composite material sheet, comprising the following steps: (1) Vacuum consumable arc melting: First, the ingredients are calculated according to the above alloy composition to determine the content of each element required for the preparation of 1000kg ingot. Then, the content of each raw material for smelting is determined based on the calculated element content, including zero-grade sponge titanium, high-purity aluminum beans, high-purity sponge zirconium, aluminum-silicon master alloy, aluminum-molybdenum master alloy, aluminum-niobium master alloy, and titanium diboride powder. A high-precision balance is used to weigh the calculated raw materials. Then, an automatic mixing system is used to uniformly mechanically mix the raw materials. The above uniformly mixed raw materials are pressed by a 6000T electrode press to obtain a consumable electrode. The pressed consumable electrode is combined and welded using a vacuum plasma welding box to obtain a combined billet. The combined billet is subjected to three vacuum consumable arc melting processes with a melting vacuum degree of ≤5Pa to obtain a particle-reinforced titanium-based composite ingot. After the ingot is subjected to riser, ingot bottom sawing and skinning treatment, a finished ingot of φ620mm is obtained.

[0030] (2) Slab forging: The ingot obtained in step (1) is subjected to one heat forging deformation at 1150°C using a fast forging machine. The ingot is heated by a step preheating method with a preheating temperature of ≥800°C. During the forging process, the ingot is wrapped with heat-insulating cotton. The total forging ratio of each fire is 7.2. The deformation speed is controlled at 20-70 mm / s. The final forging temperature is ≥950°C. After forging, the ingot is air-cooled to obtain a forged billet. After the forging is opened, the billet is heated to the preset temperature using a step heating method and then subjected to four rounds of upsetting and drawing deformation. The four fire temperatures are 1100℃, 1090℃, 1080℃ and 1070℃ respectively. The step preheating temperature is ≥800℃. During the forging process, insulation cotton is wrapped. The forging deformation speed is controlled at 20-60mm / s. The drawing process is carried out alternately along the axial and radial directions of the ingot. The total forging ratio of each fire is 8.5. The final forging temperature is ≥900℃. After forging, it is air-cooled to obtain the first-level forging billet. The first-level forging billet is reheated to 1000℃ and subjected to three rounds of upsetting and drawing deformation. The step preheating temperature is ≥800℃. During the forging process, insulation cotton is wrapped. The forging deformation speed is controlled at 10-50mm / s. The total forging ratio of each fire is 6.4. The final forging temperature is ≥850℃. After forging, it is air-cooled to obtain the second-level forging billet. The secondary forging blank is heated to 1060℃ for two rounds of slab forging and shaping. The forging deformation speed is controlled at 10~40mm / s. The forging ratio of the last round is 1.7. After forging, the blank is air-cooled to obtain a titanium-based composite material slab.

[0031] (3) Thin plate rolling: The titanium-based composite material slab obtained in step (2) is subjected to 4 rounds of rolling deformation. The rolling temperature of the first 3 rounds is 1080°C, and the holding time is determined by H×(0.8~2.0)min, where H is the total thickness of the slab, in mm. Each round is subjected to 6 rounds of deformation, with a deformation amount of 8%~35% per round, and a total deformation amount of >50% per round. After each round of deformation, the direction is reversed, and the cooling method is air cooling. After 3 rounds of rolling deformation, the slab is polished, pickled, and cut to size, and the size of the cut is determined according to the specifications of the finished plate. The cut slab is welded and clad with metal plates, and then thin plate rolling is carried out at a temperature of 1120°C after cladding. The heating time of the slab is determined by H×(0.8~1.5)min, the rolling passes are 6, and the deformation amount of the pass is controlled between 10%~40%. After air cooling, the cladding material is removed to obtain a thin plate semi-finished product.

[0032] (4) Surface treatment: The surface of the semi-finished sheet obtained in step (3) was sanded and acid-alkali washed to obtain finished sheet-structure titanium-based composite material sheets with thicknesses of 0.8 mm and 1.2 mm, respectively. The microstructure was examined using a metallographic microscope, as shown in FIG. Figure 2 shown.

[0033] Performance Testing The finished titanium-based composite material sheet prepared in Example 1-2 was subjected to performance tests. The room temperature tensile performance test standard was in accordance with GB / T 228.1-2010; the high temperature tensile performance test standard was in accordance with GB / T 228.2-2015; the endurance / creep test standard was in accordance with GB / T 2039-2012. The 650°C endurance test conditions were: 650°C / 240 MPa, the 600°C endurance test conditions were: 600°C / 200 MPa, and the creep test conditions were: 650°C / 100 MPa / 100 h. The results are shown in Tables 1 and 2 below.

[0034] Table 1 Mechanical properties of materials in Example 1 Table 2 Mechanical properties of materials in Example 2 As can be seen from the table, the yield strength of the lamellar structure titanium-based composite material thin plate prepared by the present invention at 650°C is greater than 465MPa, the sustained fracture time at 650°C / 240MPa is ≥30h, the sustained fracture time at 600°C / 200MPa is greater than 300h, and the creep residual strain at 650°C / 100MPa / 100h is less than 0.5%. Compared with traditional equiaxed high-temperature titanium alloy thin plates, the yield strength and sustained creep resistance are significantly improved.

[0035] Obviously, the above embodiments are merely examples for clarity of explanation and are not intended to limit the implementation methods. Those skilled in the art will readily appreciate that other variations or modifications based on the above descriptions are possible. It is not necessary and impossible to enumerate all implementation methods here. Obvious variations or modifications arising therefrom remain within the scope of protection of the present invention.

Claims

1. A method for preparing a lamellar titanium-based composite material sheet, characterized in that: The following steps are involved: S1. The raw materials are repeatedly remelted by vacuum consumable melting to obtain a particle-reinforced titanium-based composite ingot; S2. The ingot is forged into a slab to obtain a titanium-based composite material slab; the slab forging comprises: subjecting the ingot to open forging, performing 1 to 2 fires of open deformation at 1150-1200°C, with a total forging ratio of ≥6 for each fire, air cooling after forging, to obtain an open forged slab; subjecting the open forged slab to a primary forging process, heating it to T β ~T β +100℃ for 1~4 times of upsetting deformation, with the total forging ratio of each fire being greater than 8, and air cooling after forging to obtain a first-level forging billet; the first-level forging billet is subjected to secondary forging and heated to T β -40℃~T β +80℃ for 2~5 times of upsetting deformation, with the total forging ratio of each fire being greater than 6, and air cooling after forging to obtain a secondary forging billet; the secondary forging billet is subjected to shaping forging and heated to T β -30℃~T β The slab is deformed at +60℃ for 1~2 times with a final forging ratio of 1.2~2.0, and air-cooled after forging to obtain a titanium-based composite slab; S3 the titanium-based composite material slab by sheet rolling to obtain a sheet semi-finished product; the sheet rolling comprises: the titanium-based composite material slab rough rolling treatment, in T β -40℃~T β +50℃ for 1~4 times of rolling deformation, the holding time is H×(0.8~2.0)min, and the total deformation of the fire is ≥50%; the titanium-based composite material slab after rough rolling is welded and clad. β ~T β Finish rolling is performed at +100°C for a heating time of H×(0.8-1.5) min, and the coating material is removed after air cooling to obtain a thin semi-finished product; wherein H is the slab thickness in mm; the total number of rolling deformations in the rough rolling and finish rolling is 2-6 times; S4. Surface treatment is performed on the semi-finished thin plate to obtain the lamellar structure titanium-based composite material thin plate.

2. The method for preparing a lamellar structure titanium-based composite material sheet according to claim 1, wherein: In step S1, the raw materials include zero-grade titanium sponge, high-purity aluminum beans, high-purity zirconium sponge, aluminum-silicon master alloy, aluminum-molybdenum master alloy, aluminum-niobium master alloy, high-purity yttrium powder or aluminum-yttrium master alloy, and titanium diboride powder.

3. The method for preparing a lamellar structure titanium-based composite material sheet according to claim 1, wherein: In step S2, the deformation speed of the blanking forging is 20-70 mm / s, the deformation speed of the primary forging is 20-60 mm / s, the deformation speed of the secondary forging is 10-50 mm / s, and the deformation speed of the shaping forging is 10-40 mm / s.

4. The method for preparing a lamellar titanium-based composite material sheet according to claim 1, wherein: In step S2, during the primary forging process, iron drawing is performed alternately along the axial and radial directions of the ingot.

5. The method for preparing a lamellar structure titanium-based composite material sheet according to claim 1, wherein: In step S3, in the rough rolling process, 2 to 8 deformation passes are performed in each pass, and the deformation amount of each pass is 8% to 35%. Reversal is performed after each deformation pass.

6. The method for preparing a lamellar structure titanium-based composite material sheet according to claim 1, wherein: In step S3, the titanium-based composite material slab after the rough rolling process is first polished, pickled and cut into pieces before the finish rolling process, and the cutting size is determined according to the specifications of the finished plate.

7. The method for preparing a lamellar structure titanium-based composite material sheet according to claim 1, wherein: In step S3, in the finishing rolling process, the rolling passes are 3 to 8, and the deformation amount of each pass is controlled between 10% and 40%.

8. The method for preparing a lamellar titanium-based composite material sheet according to claim 1, wherein: In step S4, the surface treatment includes surface sanding treatment and acid and alkali cleaning treatment.

9. The method for preparing a lamellar structure titanium-based composite material sheet according to claim 1, wherein: The chemical composition of the lamellar structure titanium-based composite material sheet is as follows: Al: 6.2wt%~6.9wt%, Sn: 1.1wt%~3.5wt%, Zr: 2.3wt%~10.5wt%, Mo: 0.3wt%~2.3wt%, Nb: 0.7wt%~2.5wt%, Si: 0.2wt%~0.6wt%, O: 0.05wt%~0.15wt%, B: 0.12wt%~0.7wt%, Y: ≤0.3wt%, C: ≤0.1wt%, Fe: ≤0.035wt%, and the balance is Ti, among which the contents of Al, Sn, and Zr satisfy: (Al+Sn / 3+Zr / 6)≤8.

8.

10. A lamellar titanium-based composite material sheet, characterized in that: The lamellar structure titanium-based composite material sheet is prepared according to the preparation method of any one of claims 1 to 9.

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