CN115650755B - A 3D printing method for preparing continuous fiber toughened silicon carbide ceramic matrix composites - Google Patents

Abstract

The invention discloses a method for preparing a continuous fiber toughened silicon carbide ceramic matrix composite material by 3D printing, which belongs to the technical field of 3D printing. The preparation method includes the following steps: (1) using the continuous fiber prepreg impregnated with resin as a printing filament, performing 3D printing to obtain a continuous fiber reinforced resin matrix composite material, and then performing carbonization and cracking to obtain a continuous fiber block preform (2) sequentially depositing pyrolytic carbon and SiC matrix on the continuous fiber bulk preform to obtain continuous fiber toughened silicon carbide ceramic matrix composite material. The present invention adopts 3D printing-assisted chemical vapor deposition technology to prepare continuous fiber reinforced SiC ceramic matrix composite material, which greatly simplifies the weaving link of ceramic matrix composite material prefabricated body, and the prepared material has phase stability, high temperature resistance, high strength and resistance Oxidation and other advantages have great application prospects in the fields of aerospace equipment and brakes.

Description

A 3D printing method for preparing continuous fiber toughened silicon carbide ceramic matrix composites

technical field

The invention relates to the technical field of 3D printing, in particular to a method for preparing a continuous fiber toughened silicon carbide ceramic matrix composite material by 3D printing.

Background technique

Continuous fiber reinforced silicon carbide ceramic matrix composites are one of the most potential materials for preparing thermal structural parts in the fields of aviation, aerospace and brakes. They have low density, high thermal conductivity, friction resistance, thermal shock resistance and low thermal expansion coefficient, etc. A range of advantages. However, due to the problems of high hardness and difficulty in processing of continuous fiber reinforced silicon carbide ceramic matrix composites, continuous fiber reinforced silicon carbide ceramic matrix composite components are generally prepared by means of near-shape molding. Preform weaving is the main method for continuous fiber toughened ceramic matrix composites to form near-shape dimensions. Currently, the main weaving methods for continuous fiber preforms include fiber cloth lamination and three-dimensional weaving technology; fiber cloth lamination technology is simple to operate, but requires Prepare continuous fiber cloth in advance; the fiber prefabricated body prepared by three-dimensional weaving technology is not easy to disintegrate between layers due to the shackles of isotropic fibers, but the weaving equipment is relatively complicated and the weaving cycle is too long. At the same time, in the three-dimensional weaving process, it is more difficult to increase or decrease the yarn of the preform, which will further prolong the forming cycle of the preform and affect the preparation efficiency of the composite material.

Contents of the invention

The purpose of the present invention is to provide a method for preparing continuous fiber toughened silicon carbide ceramic matrix composites by 3D printing to solve the problems in the prior art. The 3D printing used in the present invention prepares continuous fiber toughened silicon carbide ceramic matrix composites The method of the material is simple in process, low in cost, and has broad application prospects, and the prepared continuous fiber toughened silicon carbide ceramic matrix composite material can improve the molding efficiency of the near-shape size of the prefabricated body.

To achieve the above object, the present invention provides the following scheme:

One of the technical solutions of the present invention: a method for preparing a continuous fiber toughened silicon carbide ceramic matrix composite material by 3D printing, comprising the following steps:

(1) Use 3D modeling software to complete the model construction of the sample, set the 3D printing path, use the continuous fiber prepreg impregnated with resin (binder) as the printing filament, and perform 3D printing to obtain the continuous fiber reinforced resin matrix. Composite materials, followed by carbonization and cracking to obtain continuous fiber block preforms;

(2) sequentially depositing (chemical vapor deposition) pyrolytic carbon and SiC matrix on the continuous fiber bulk preform to obtain a continuous fiber toughened silicon carbide ceramic matrix composite material.

Further, in step (1), the resin includes phenolic resin, epoxy resin or nylon resin; the continuous fiber prepreg includes carbon fiber (C _f ) or silicon carbide fiber (SiC _f ).

Further, in step (1), the conditions of the 3D printing are: the printing temperature of the resin binder (nylon 66) is 100-250°C, and the printing speed is 30-80cm/s; the printing temperature of the printing filament is 150～300℃, printing speed is 1～10cm/s.

Further, in step (1), the volume fraction of the continuous fiber prepreg in the printing filament is ≥60%.

Further, in step (1), the temperature of the carbonization cracking (heat treatment) is 600-1000°C, the holding time is 1h, the flow rate of the protective gas is 600-800mL/min, and the heating rate and cooling rate are both 5°C/min. min.

Further, in step (2), the temperature of the deposited pyrolytic carbon is 900-1200°C, the pressure is 1-3kPa, the deposition time is 3-10h, and the flows of protective gas and methane are both 800-2000mL/min , the heating rate is 5°C/min, and the cooling rate is 7°C/min.

Further, the feed rate of the deposited SiC matrix precursor is 1-4g/min, the heating rate is 5°C/min, the deposition temperature is 900-1300°C, the deposition time is 200-400h, and the reducing gas flow rate during heating is The temperature is 1000-3000mL/min, the protective gas flow rate is 800-3000mL/min, the pressure is 1-10kPa, the cooling rate is 7°C/min, and the protective gas flow rate during cooling is 1000mL/min.

Further, the precursor includes methyltrichlorosilane; the reducing gas is hydrogen, and the protective gas is argon.

The second technical solution of the present invention: a continuous fiber toughened silicon carbide ceramic matrix composite material prepared by the above method.

The third technical solution of the present invention: an application of the above-mentioned continuous fiber toughened silicon carbide ceramic matrix composite material in the preparation of special-shaped components.

The invention discloses the following technical effects:

(1) The present invention uses a 3D printer to print the continuous fiber prepreg filament containing resin into a resin-based composite material, and then through carbonization and cracking, the resin material is converted into pyrolytic carbon to play the role of bonding fibers and obtain Continuous fiber block preform. Then, the PyC interface phase and SiC matrix are deposited on the preform by chemical vapor deposition technology, so as to obtain the continuous fiber reinforced SiC ceramic matrix composite material, which greatly simplifies the weaving process of the ceramic matrix composite material preform.

(2) Adopting the preparation method of the present invention can overcome the problem that for thermal components with different shapes, the more complex the shape, the more cumbersome the weaving process, which leads to a substantial increase in manufacturing costs, and the rapid prototyping of complex component prefabricated bodies of ceramic matrix composites can be realized , greatly reducing the preparation cycle and production costs.

Description of drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the accompanying drawings required in the embodiments. Obviously, the accompanying drawings in the following description are only some of the present invention. Embodiments, for those of ordinary skill in the art, other drawings can also be obtained based on these drawings without any creative effort.

Fig. 1 is a schematic diagram of the 3D printing path of Example 1 of the present invention, wherein (a) is the printing path of odd-numbered layers of fibers; (b) is the printing path of even-numbered layers of fibers;

Figure 2 is a process diagram of preparing continuous fiber toughened silicon carbide ceramic matrix composite material in Example 1 of the present invention, wherein (a) is a continuous fiber reinforced resin matrix composite material sample (cuboid 3D printing), (b) is continuous fiber Toughened silicon carbide ceramic matrix composite material, (c) is a macroscopic photo of continuous fiber toughened silicon carbide ceramic matrix composite material;

Figure 3 is an SEM image of the process of preparing continuous fiber toughened silicon carbide ceramic matrix composite material in Example 1 of the present invention, wherein (a) is a continuous fiber block preform, and (b) is a preform with a PyC interface phase (C _f @PyC), (c) is continuous fiber toughened silicon carbide ceramic matrix composite (C _f @PyC/SiC), (d) is the fracture morphology of C _f @PyC, (e) is C _f @PyC /SiC fracture morphology;

4 is a schematic diagram of the 3D printing path of Embodiment 2 of the present invention;

Fig. 5 is a process diagram of preparing continuous fiber toughened silicon carbide ceramic matrix composite material in Example 2 of the present invention, wherein (a) is a continuous fiber reinforced resin matrix composite material sample (3D printing of complex special-shaped components), (b) is Continuous fiber toughened silicon carbide ceramic matrix composite material, (c) is a macroscopic photo of continuous fiber toughened silicon carbide ceramic matrix composite material;

Fig. 6 is a graph showing the bending test results of the continuous fiber toughened silicon carbide ceramic matrix composite material prepared in Example 1 of the present invention.

Detailed ways

Various exemplary embodiments of the present invention will now be described in detail. The detailed description should not be considered as a limitation of the present invention, but rather as a more detailed description of certain aspects, features and embodiments of the present invention.

It should be understood that the terminology described in the present invention is only used to describe specific embodiments, and is not used to limit the present invention. In addition, regarding the numerical ranges in the present invention, it should be understood that each intermediate value between the upper limit and the lower limit of the range is also specifically disclosed. Each smaller range between any stated value or intervening value in a stated range and any other stated value or intervening value in a stated range is encompassed within the invention. The upper and lower limits of these smaller ranges may independently be included or excluded from the range.

Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. Although only the preferred methods and materials are described herein, any methods and materials similar or equivalent to those described herein can be used in the practice or testing of the present invention. All documents mentioned in this specification are incorporated by reference to disclose and describe the methods and materials in connection with which the documents are described. In case of conflict with any incorporated document, the contents of this specification control.

It will be apparent to those skilled in the art that various modifications and changes can be made in the specific embodiments of the present invention described herein without departing from the scope or spirit of the present invention. Other embodiments will be apparent to the skilled person from the description of the present invention. The specification and examples in this application are exemplary only.

As used herein, "comprising", "comprising", "having", "comprising" and so on are all open terms, meaning including but not limited to.

The purity of methyltrichlorosilane (MTS) used in the following examples and comparative examples of the present invention is greater than 99.90%, the purity of methane gas is greater than 99.90%, and the purity of hydrogen and argon is greater than 99.999%.

Example 1

A method for preparing continuous fiber toughened silicon carbide ceramic matrix composites by 3D printing:

(1) Preparation of continuous fiber-reinforced resin-based composite material samples: use 3D modeling software to complete the model construction of the sample, set the 3D printing path (see Figure 1), and impregnate the carbon fiber in the molten phenolic resin for an immersion time of 5min, cooling after impregnation is completed, obtain printing filament material (the volume fraction of carbon fiber in the printing filament material is 60%), then adopt this printing filament material to carry out 3D printing, print filament material (printing filament material: resin binder=19: 1) The printing temperature is 265°C, the printing speed is 10mm/s, the printing temperature of the resin binder (nylon 66) is 250°C, and the printing speed is 50mm/s. The diameter of the basic nozzle is 0.4 mm, the temperature of the printing platform is 60 ° C, and 60 layers are printed to obtain a continuous fiber reinforced resin matrix composite material sample.

(2) Preparation of continuous fiber block preform: fix the continuous fiber reinforced resin matrix composite material sample with graphite paper, place it in a graphite crucible, and then put it into a heat treatment furnace for carbonization and cracking to control the carbonization and cracking The conditions are: argon (Ar) is introduced as a protective gas (gas flow rate is 600mL/min), the temperature is raised to 700°C at a heating rate of 5°C/min, kept for 1h, and then cooled to room temperature at a cooling rate of 5°C/min , to obtain a continuous fiber block preform.

(3) Depositing pyrolytic carbon (depositing PyC interface phase): the continuous fiber block preform is placed in an isothermal chemical vapor deposition furnace to deposit pyrolytic carbon. The conditions for depositing pyrolytic carbon are: argon gas is introduced as a protective gas ( The gas flow rate is 800-2000mL/min), the deposition pressure is controlled at 1kPa, the temperature is raised to 1000°C at a heating rate of 5°C/min, and then methane gas (CH ₄ , gas flow rate is 800-2000mL/min) is introduced for deposition and pyrolysis Carbon, the deposition time is 3h. After the deposition is completed, the temperature is lowered to room temperature at a cooling rate of 7°C/min to obtain a preform with a PyC interface phase.

(4) Deposit SiC matrix: place the prefabricated body with PyC interface phase in the constant temperature zone of the isothermal chemical vapor deposition furnace to deposit SiC matrix. 3000mL/min), control the pressure in the furnace to 1.8kPa, raise the temperature to 1100°C at a heating rate of 5°C/min, feed _H2 as a reducing gas (gas flow rate is 1000-3000mL/min), and then carry out the precursor (Methyltrichlorosilane, MTS) feeding (rate 2g/min) to deposit SiC matrix, the deposition time is 400h, stop feeding H ₂ after the deposition is completed, change the gas flow rate of the protective gas to 1000mL/min, with 7 The cooling rate of ℃/min was lowered to room temperature, and the continuous fiber toughened silicon carbide ceramic matrix composite material was obtained. The preparation process diagram is shown in Figure 2, and the SEM image is shown in Figure 3.

In Fig. 2, (a) is the continuous fiber reinforced resin matrix composite material sample (cuboid 3D printing), (b) is the continuous fiber toughened silicon carbide ceramic matrix composite material, (c) is the continuous fiber toughened silicon carbide ceramic matrix Macro photo of composite material.

In Fig. 3, (a) is the continuous fiber bulk preform, (b) is the preform with PyC interface phase (C _f @PyC), (c) is the continuous fiber toughened silicon carbide ceramic matrix composite (C _f @PyC/SiC), (d) is the fracture morphology of C _f @PyC, (e) is the fracture morphology of C _f @PyC/SiC composite.

It can be seen from Figure 2 that the fiber preform can be formed by 3D printing, and a continuous fiber preform can be obtained after heat treatment; it can be seen from Figure 3 that after the deposition of the PyC interface phase and the SiC matrix, PyC and SiC The two phases of SiC are completely covered on the surface of the carbon fiber, the interface is well bonded, and there is no obvious shedding phenomenon.

Example 2

A method for preparing continuous fiber toughened silicon carbide ceramic matrix composites by 3D printing:

(1) Preparation of continuous fiber-reinforced resin-based composite material samples: use 3D modeling software to complete the model construction of the sample, set the 3D printing path (see Figure 4), impregnate the silicon carbide fiber in molten epoxy resin, The immersion time is 5min, cooling after the immersion is completed, and the printing filament is obtained (the volume fraction of silicon carbide fiber in the printing filament is 70%), and then the printing filament is used for 3D printing (printing filament: resin binder=19 : 1), the printing temperature of the printing filament is 230°C, the printing speed is 6mm/s, the printing temperature of the resin binder (nylon 66) is 240°C, and the printing speed is 80mm/s. The diameter of the basic nozzle is 0.4 mm, the temperature of the printing platform is 50 ° C, and 90 layers are printed to obtain a continuous fiber reinforced resin matrix composite material sample.

(2) Preparation of continuous fiber block preform: fix the continuous fiber reinforced resin matrix composite material sample with graphite paper, place it in a graphite crucible, and then put it into a heat treatment furnace for carbonization and cracking to control the carbonization and cracking The conditions are: argon (Ar) is introduced as a protective gas (gas flow rate is 800mL/min), the temperature is raised to 1000°C at a heating rate of 5°C/min, kept for 1h, and then cooled to room temperature at a cooling rate of 5°C/min , to obtain a continuous fiber block preform.

(3) Depositing pyrolytic carbon (depositing PyC interface phase): the continuous fiber block preform is placed in an isothermal chemical vapor deposition furnace to deposit pyrolytic carbon. The conditions for depositing pyrolytic carbon are: argon gas is introduced as a protective gas ( The gas flow rate is 800-2000mL/min), the deposition pressure is controlled at 2kPa, the temperature is raised to 1000°C at a heating rate of 5°C/min, and then methane gas (CH ₄ , gas flow rate is 800-2000mL/min) is introduced for deposition and pyrolysis Carbon, the deposition time is 3h. After the deposition is completed, the temperature is lowered to room temperature at a cooling rate of 7°C/min to obtain a preform with a PyC interface phase.

(4) Deposit SiC matrix: place the prefabricated body with PyC interface phase in the constant temperature zone of the isothermal chemical vapor deposition furnace to deposit SiC matrix. 3000mL/min), control the pressure in the furnace to 1kPa, raise the temperature to 1100°C at a heating rate of 5°C/min, feed _H2 as a reducing gas (gas flow rate is 1000-3000mL/min), and then carry out the precursor ( Methyltrichlorosilane, MTS) was fed (at a rate of 1 g/min) to deposit the SiC substrate, and the deposition time was 300 h. After the deposition was completed, H ₂ was stopped, and the gas flow rate of the protective gas was changed to 1000 mL/min. /min cooling rate to cool down to room temperature to obtain a continuous fiber toughened SiC ceramic matrix composite material, the preparation process diagram is shown in Figure 5.

In Fig. 5, (a) is a continuous fiber reinforced resin matrix composite material sample (3D printing of complex special-shaped components), (b) is a continuous fiber toughened silicon carbide ceramic matrix composite material, (c) is a continuous fiber toughened silicon carbide Macrophotograph of ceramic matrix composites.

It can be seen from Figure 5 that the molding of the fiber preform can be completed by 3D printing, and the continuous fiber preform (complex special-shaped component) is obtained after heat treatment.

Example 3

A method for preparing continuous fiber toughened silicon carbide ceramic matrix composites by 3D printing:

(1) Preparation of continuous fiber-reinforced resin-based composite material sample: use 3D modeling software to complete the model construction of the sample, set the 3D printing path (as shown in Figure 4), and impregnate silicon carbide fibers (fiber volume fraction is 60%) In the molten nylon resin, the immersion time is 5min. After the immersion is completed, it is cooled to obtain a printing filament (the volume fraction of silicon carbide fiber in the printing filament is 70%), and then the printing filament is used for 3D printing (printing filament : resin binder=19:1), the printing temperature of the printing filament is 270°C, the printing speed is 9mm/s, the printing temperature of the resin binder is 210°C, and the printing speed is 100mm/s. The diameter of the basic nozzle is 0.4mm, the temperature of the printing platform is 40°C, and 90 layers are printed to obtain a continuous fiber reinforced resin matrix composite material sample.

(2) Preparation of continuous fiber block preform: fix the continuous fiber reinforced resin matrix composite material sample with graphite paper, place it in a graphite crucible, and then put it into a heat treatment furnace for carbonization and cracking to control the carbonization and cracking The conditions are: argon (Ar) is introduced as a protective gas (gas flow rate is 600mL/min), the temperature is raised to 800°C at a heating rate of 5°C/min, kept for 1h, and then cooled to room temperature at a cooling rate of 5°C/min , to obtain a continuous fiber block preform.

(3) Depositing pyrolytic carbon (depositing PyC interface phase): the continuous fiber block preform is placed in an isothermal chemical vapor deposition furnace to deposit pyrolytic carbon. The conditions for depositing pyrolytic carbon are: argon gas is introduced as a protective gas ( The gas flow rate is 800-2000mL/min), the deposition pressure is controlled at 2kPa, the temperature is raised to 1100°C at a heating rate of 5°C/min, and then methane gas (CH ₄ , gas flow rate is 800-2000mL/min) is introduced for deposition and pyrolysis Carbon, the deposition time is 3h. After the deposition is completed, the temperature is lowered to room temperature at a cooling rate of 7°C/min to obtain a preform with a PyC interface phase.

(4) Deposit SiC matrix: place the prefabricated body with PyC interface phase in the constant temperature zone of the isothermal chemical vapor deposition furnace to deposit SiC matrix. 3000mL/min), control the pressure in the furnace to 3kPa, raise the temperature to 1200°C at a heating rate of 5°C/min, feed _H2 as a reducing gas (gas flow rate is 1000-3000mL/min), and then carry out the precursor ( Methyltrichlorosilane, MTS) was fed (at a rate of 3 g/min) to deposit the SiC substrate, and the deposition time was 200 h. After the deposition was completed, H ₂ was stopped, and the gas flow rate of the protective gas was changed to 1000 mL/min. /min cooling rate to cool down to room temperature to obtain continuous fiber toughened silicon carbide ceramic matrix composites.

Example 4

Same as Example 1, the difference is that the carbonization cracking temperature in step (2) is 600°C.

Example 5

Same as Example 1, the difference is that the temperature for depositing pyrolytic carbon in step (3) is 1200° C., the deposition pressure is 3 kPa, and the deposition time is 10 h.

Example 6

Same as Example 1, the difference is that the temperature for depositing the SiC matrix in step (3) is 900°C.

Example 7

Same as Example 1, the difference is that the temperature for depositing the SiC matrix in step (3) is 1300° C., the pressure in the furnace is 10 kPa, and the feed rate of the precursor is 4 g/min.

Effect Example 1

The bending performance test of the continuous fiber-reinforced silicon carbide ceramic matrix composite material prepared by the method of the present invention shows that its bending resistance reaches 180±10MPa. The stress-strain spectrum is shown in Fig. 6.

The above-mentioned embodiments are only to describe the preferred mode of the present invention, and are not intended to limit the scope of the present invention. Variations and improvements should fall within the scope of protection defined by the claims of the present invention.

Claims (5)

1. The method for preparing the continuous fiber toughened silicon carbide ceramic matrix composite by 3D printing is characterized by comprising the following steps of:

(1) Preparation of continuous fiber reinforced resin matrix composite samples: 3D printing paths are set, carbon fibers are immersed in molten phenolic resin for 5min, and cooled after the immersion is finished, so that printing wires are obtained, and the volume fraction of the carbon fibers in the printing wires is 60%; then 3D printing is carried out by adopting the printing wire, the ratio of the printing wire to the resin binder is 19:1, the printing temperature of the printing wire is 265 ℃, and the printing speed is 10mm/s; the resin binder is nylon 66, the printing temperature of the resin binder is 250 ℃, and the speed is 50mm/s; the diameter of the basic nozzle is 0.4mm, the temperature of the printing platform is 60 ℃, and 60 layers are printed to obtain a continuous fiber reinforced resin matrix composite sample;

(2) Preparation of continuous fiber block preform: fixing a continuous fiber reinforced resin matrix composite sample by using graphite paper, placing the sample into a graphite crucible, and then placing the sample into a heat treatment furnace for carbonization and pyrolysis, wherein the conditions for carbonization and pyrolysis are as follows: argon is introduced as shielding gas, the temperature is raised to 700 ℃ at a heating rate of 5 ℃/min, the temperature is kept for 1h, and then the temperature is lowered to room temperature at a cooling rate of 5 ℃/min, so that a continuous fiber block-shaped preform is obtained;

(3) Depositing pyrolytic carbon: placing the continuous fiber block preform in an isothermal chemical vapor deposition furnace to deposit pyrolytic carbon, wherein the pyrolytic carbon deposition conditions are as follows: argon is introduced as shielding gas, the deposition pressure is controlled to be 1kPa, the temperature is raised to 1000 ℃ at the heating rate of 5 ℃/min, then methane gas is introduced to deposit pyrolytic carbon, the deposition time is 3h, and after the deposition is completed, the temperature is reduced to room temperature at the cooling rate of 7 ℃/min, so as to obtain a preform with a PyC interface phase;

(4) Depositing a SiC matrix: placing the preform with the PyC interface phase in a constant temperature zone in an isothermal chemical vapor deposition furnace to deposit the SiC matrix, wherein the conditions for depositing the SiC matrix are as follows: argon is introduced as shielding gas, the pressure in the hearth is controlled to be 1.8kPa, the temperature is raised to 1100 ℃ at the heating rate of 5 ℃/min, and H is introduced ₂ As reducing gas, then precursor feeding is carried out to deposit SiC matrix for 400H, and after the deposition is completed, the H is stopped to be introduced ₂ Changing the gas flow of the shielding gas into 1000mL/min, and cooling to room temperature at the cooling rate of 7 ℃/min to obtain the continuous fiber toughened silicon carbide ceramic matrix composite.

2. The method for preparing the continuous fiber toughened silicon carbide ceramic matrix composite by 3D printing is characterized by comprising the following steps of:

(1) Preparation of continuous fiber reinforced resin matrix composite samples: 3D printing paths are set, silicon carbide fibers are immersed in molten epoxy resin for 5min, and cooled after the immersion is finished, so that printing wires are obtained, and the volume fraction of the silicon carbide fibers in the printing wires is 70%; then 3D printing is carried out by adopting the printing wire, the ratio of the printing wire to the resin binder is 19:1, the printing temperature of the printing wire is 230 ℃, and the printing speed is 6mm/s; the resin binder is nylon 66, the printing temperature of the resin binder is 240 ℃, and the speed is 80mm/s; the diameter of the basic nozzle is 0.4mm, the temperature of the printing platform is 50 ℃, and 90 layers are printed to obtain a continuous fiber reinforced resin matrix composite sample;

(2) Preparation of continuous fiber block preform: fixing a continuous fiber reinforced resin matrix composite sample by using graphite paper, placing the sample into a graphite crucible, and then placing the sample into a heat treatment furnace for carbonization and pyrolysis, wherein the conditions for carbonization and pyrolysis are as follows: argon is introduced as shielding gas, the temperature is raised to 1000 ℃ at the heating rate of 5 ℃/min, the heat is preserved for 1h, and then the temperature is reduced to room temperature at the cooling rate of 5 ℃/min, so that a continuous fiber block-shaped preform is obtained;

(3) Depositing pyrolytic carbon: placing the continuous fiber block preform in an isothermal chemical vapor deposition furnace to deposit pyrolytic carbon, wherein the pyrolytic carbon deposition conditions are as follows: argon is introduced as shielding gas, the deposition pressure is controlled to be 2kPa, the temperature is raised to 1000 ℃ at the heating rate of 5 ℃/min, then methane gas is introduced to deposit pyrolytic carbon, the deposition time is 3h, and after the deposition is completed, the temperature is reduced to room temperature at the cooling rate of 7 ℃/min, so as to obtain a preform with a PyC interface phase;

(4) Depositing a SiC matrix: placing the preform with the PyC interface phase in a constant temperature zone in an isothermal chemical vapor deposition furnace to deposit the SiC matrix, wherein the conditions for depositing the SiC matrix are as follows: argon is introduced as shielding gas, the pressure in the hearth is controlled to be 1kPa, the temperature is raised to 1100 ℃ at the heating rate of 5 ℃/min, and H is introduced ₂ As reducing gas, then precursor feeding is carried out to deposit SiC matrix, the deposition time is 300H, and after the deposition is finished, the H is stopped being introduced ₂ Changing the gas flow of the shielding gas into 1000mL/min, and cooling to room temperature at the cooling rate of 7 ℃/min to obtain the continuous fiber toughened silicon carbide ceramic matrix composite.

3. The method for preparing the continuous fiber toughened silicon carbide ceramic matrix composite by 3D printing is characterized by comprising the following steps of:

(1) Preparation of continuous fiber reinforced resin matrix composite samples: 3D printing paths are set, silicon carbide fibers with the fiber volume fraction of 60% are immersed in molten nylon resin for 5min, and the impregnated silicon carbide fibers are cooled after the immersion is completed, so that printing wires are obtained, and the volume fraction of the silicon carbide fibers in the printing wires is 70%; then 3D printing is carried out by adopting the printing wire, the ratio of the printing wire to the resin binder is 19:1, the printing temperature of the printing wire is 270 ℃, and the printing speed is 9mm/s; the printing temperature of the resin binder is 210 ℃ and the speed is 100mm/s; the diameter of the basic nozzle is 0.4mm, the temperature of the printing platform is 40 ℃, and 90 layers are printed to obtain a continuous fiber reinforced resin matrix composite sample;

(2) Preparation of continuous fiber block preform: fixing a continuous fiber reinforced resin matrix composite sample by using graphite paper, placing the sample into a graphite crucible, and then placing the sample into a heat treatment furnace for carbonization and pyrolysis, wherein the conditions for carbonization and pyrolysis are as follows: argon is introduced as shielding gas, the temperature is raised to 800 ℃ at the heating rate of 5 ℃/min, the heat is preserved for 1h, and then the temperature is lowered to room temperature at the cooling rate of 5 ℃/min, so that a continuous fiber block-shaped preform is obtained;

(3) Depositing pyrolytic carbon: placing the continuous fiber block preform in an isothermal chemical vapor deposition furnace to deposit pyrolytic carbon, wherein the pyrolytic carbon deposition conditions are as follows: argon is introduced as shielding gas, the deposition pressure is controlled to be 2kPa, the temperature is raised to 1100 ℃ at the heating rate of 5 ℃/min, then methane gas is introduced to deposit pyrolytic carbon for 3 hours, and after the deposition is completed, the temperature is reduced to room temperature at the cooling rate of 7 ℃/min, so as to obtain a preform with a PyC interface phase;

(4) Depositing a SiC matrix: placing the preform with the PyC interface phase in a constant temperature zone in an isothermal chemical vapor deposition furnace to deposit the SiC matrix, wherein the conditions for depositing the SiC matrix are as follows: argon is introduced as protective gas, the pressure in the hearth is controlled to be 3kPa, the temperature is raised to 1200 ℃ at the heating rate of 5 ℃/min, and H is introduced ₂ As reducing gas, then precursor feeding is carried out to deposit SiC matrix, the deposition time is 200H, and after the deposition is completed, the H is stopped being introduced ₂ Changing the gas flow of the shielding gas into 1000mL/min, and cooling to room temperature at the cooling rate of 7 ℃/min to obtain the continuous fiber toughened silicon carbide ceramic matrix composite.

4. A continuous fiber toughened silicon carbide ceramic matrix composite prepared according to the method of any of claims 1 to 3.

5. Use of the continuous fiber toughened silicon carbide ceramic matrix composite of claim 4 in the preparation of profiled members.