A kind of preparation method of self-healing silicon carbide fiber reinforced silicon boron nitride carbon composite material

A technology of silicon-boron-nitrogen-carbon and composite materials, which is applied in the field of preparation of self-healing silicon carbide fiber-reinforced silicon-boron-nitrogen-carbon composite materials, can solve the problem of strength, toughness and reliability of thermal structural parts, ceramic matrix composite materials There are no problems such as self-healing and SiBNC fiber preparation difficulties, and achieve excellent self-healing, high-temperature mechanical properties, and low thermal expansion coefficient.

Inactive Publication Date: 2016-09-07
DONGHUA UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The disadvantage is that the prepared ceramic matrix composite material has no self-healing property. Under the action of strong alternating thermal load, the material is prone to cracks and cannot be repaired in time to break, and the service life is low.
And because SiBNC fiber is difficult to prepare, the cost is high, and it is not easy to form a prefabricated part. Using SiBNC short fiber as a reinforcing phase cannot effectively solve the problem of strength, toughness and reliability as a thermal structural part.

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0023] Prepare a polysilaborazane anhydrous toluene solution with a concentration of 70%, transfer the prepared solution to a high-temperature tube furnace protected by nitrogen, and raise the temperature in the furnace from room temperature to 150°C at a rate of 1°C / min and keep the temperature constant Heating for 1h for cross-linking treatment. The cross-linked SiBNC ceramic precursor is ground and screened with a 60-mesh screen to obtain SiBNC ceramic powder with a particle size of 100 μm. The type of SiC preform is 2.5-dimensional weaving, and the fiber volume fraction is controlled to 40%. Place the SiC fiber prefabricated parts in a mold, heat press in a hot pressing device at 200°C for 2 hours, and release the mold after cooling to obtain a silicon carbide fiber-reinforced silicon boron nitrogen carbon composite material. The composite material was heated up to 1400 °C at a rate of 1 °C / min under nitrogen flow for 2 h to crack and ceramize, and then the ceramicized sil...

Embodiment 2

[0025] Prepare a polysilaborazane anhydrous toluene solution with a concentration of 85%, transfer the prepared solution to a high-temperature tube furnace protected by nitrogen, and raise the temperature in the furnace from room temperature to 190°C at a rate of 5°C / min and keep the temperature constant Heating for 2h for cross-linking treatment. The cross-linked SiBNC ceramic precursor is ground and screened with a 60-mesh screen to obtain SiBNC ceramic powder with a particle size of 200 μm. The type of SiC fiber preform is 3-dimensional weaving, and the fiber volume fraction is controlled to 45%. The ground SiBNC ceramic powder Place the SiC fiber prefabricated parts in a mold, heat press in a hot pressing device at 215°C for 2.5 hours, and demould after cooling to obtain a silicon carbide fiber reinforced silicon boron nitrogen carbon composite material. The composite material was heated up to 1500°C at a rate of 5°C / min under a nitrogen flow for 3.5 hours to crack and cer...

Embodiment 3

[0027] Prepare a polysilaborazane anhydrous toluene solution with a concentration of 100%, transfer the prepared solution to a high-temperature tube furnace protected by nitrogen, and raise the temperature in the furnace from room temperature to 230°C at a rate of 10°C / min and keep the temperature constant Heating for 3h for cross-linking treatment. The cross-linked SiBNC ceramic precursor was ground and screened with a 60-mesh screen to obtain SiBNC ceramic powder with a particle size of 300 μm. The type of SiC fiber preform was 3-dimensional weaving, and the fiber volume fraction was controlled to 52%. The ground SiBNC ceramic powder Place the SiC fiber prefabricated parts in a mold, heat press in a hot pressing device at 230°C for 3 hours, and release the mold after cooling to obtain a silicon carbide fiber-reinforced silicon boron nitrogen carbon composite material. The composite material was heated up to 1600°C at a rate of 10°C / min under a nitrogen flow for 5 hours to be...

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Abstract

The invention relates to a preparation method of a self-healing silicon-carbide-fiber-reinforced silicon-boron-nitrogen-carbon composite material, which comprises the following steps: (1) preparing a polyborosilazane (PBSZ) precursor; dissolving the PBSZ precursor in a toluene solution under the protection of N2 to obtain a PBSZ toluene solution; transferring into a pipe furnace, crosslinking under the protection of N2, grinding and screening to obtain SiBNC precursor powder; (2) preparing SiC fibers into a prefabricated part, carrying out hot pressing on the SiBNC precursor powder and SiC fiber prefabricated part, cooling and demolding to obtain a composite material; and transferring into a pipe furnace in an N2 protective atmosphere to perform ceramization, and finally, sintering. The method is simple in technique, easy to operate and low in cost; and the prepared silicon-carbide-fiber-reinforced silicon-boron-nitrogen-carbon composite material is uniform and compact, has the advantages of favorable high-temperature stability and excellent oxidation resistance, and especially has self-healing performance.

Description

technical field [0001] The invention belongs to the field of silicon-boron-nitrogen-carbon composite materials, and in particular relates to a preparation method of self-healing silicon carbide fiber reinforced silicon-boron-nitrogen-carbon composite materials. Background technique [0002] With the leap-forward progress of aerospace technology in recent years, higher requirements are put forward for the performance of high-temperature ceramic composite materials. Among them, the effective service time of high-temperature ceramic matrix composites is an important indicator of service in aerospace high-temperature oxidation environments. The damage of a spacecraft usually begins with tiny cracks in its key materials. These cracks generally appear below the surface of the material, with hidden locations and small sizes that cannot be directly observed. After the cracks are formed, they will continue to grow under load, which will greatly weaken the bearing capacity of the mat...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C04B35/80C04B35/58C04B35/622
Inventor 余木火张晨宇刘勇柯盛包
Owner DONGHUA UNIV
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