Laminated C/S-SiC-ZrB2 composite material and preparation method thereof

A technology of c-sic-zrb2, composite material, applied in the field of laminated structure C/C-SiC-ZrB2 composite material and its preparation, can solve the problem of the increase of the overall density of the material, the limited contribution of the ablation performance, and the increase of the weight of the thermal protection system and other problems, to achieve the effect of improving ultra-high temperature oxidation resistance and improving ultra-high temperature structural strength

Active Publication Date: 2018-06-05
INST OF METAL RESEARCH - CHINESE ACAD OF SCI
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the introduction of UHTC will increase the overall density of the material and increase the weight of the thermal protection system, while the ablation of the material only occurs on the surface, and the ultra-high temperature ceramics introduced inside have limited contribution to the ablation performance

Method used

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  • Laminated C/S-SiC-ZrB2 composite material and preparation method thereof
  • Laminated C/S-SiC-ZrB2 composite material and preparation method thereof
  • Laminated C/S-SiC-ZrB2 composite material and preparation method thereof

Examples

Experimental program
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Effect test

Embodiment 1

[0032] Choose 380×80×10mm, the density is 0.5g / cm 3 The 2D needle-punched carbon fiber preform; the pyrolytic carbon interface layer was prepared by ICVI process, the temperature was 900 ° C, and the flow rate of argon gas was 0.2 m 3 / h, propane 0.15m 3 / h, the deposition time is 5 hours; the E-CVI process is used to prepare the C / C composite material with a dense center and porous sides, the temperature is 700-1000 °C, the flow ratio of argon: propane is 2:1, and the deposition time is 7 hours; SiC matrix is ​​deposited by E-CVI process, hydrogen, argon and trichloromethylsilane are introduced into the E-CVI furnace, the volume ratio is 5:5:1, the temperature is 700-1000°C, and the desired gradient structure is obtained after deposition for 15 hours C / C-SiC composite material; after adopting CNC machining and forming, ultrasonic cleaning; adopting PIP process to introduce ZrB 2 - SiC ultra-high temperature ceramic phase, after 2 cycles of impregnation and cracking, the spe...

Embodiment 2

[0034] Adopt 380×80×14mm, density is 0.51g / cm 3 The 2D needle-punched carbon fiber; the pyrolytic carbon interface layer was prepared by ICVI process, the temperature was 900°C, and the flow rate of argon gas was 0.2m 3 / h, propane 0.15m 3 / h, the deposition time is 6 hours; the C / C gradient material is prepared by E-CVI process, the temperature is 700-1000 °C, the flow ratio of argon:propane is 2:1, and the deposition time is 10 hours; the SiC substrate is deposited by E-CVI process , put hydrogen, argon and trichloromethylsilane into the E-CVI furnace, the volume ratio is 5:4:1, the temperature is 700-1000°C, and the composite material with the required laminated structure is obtained after deposition for 28 hours; CNC machining is adopted After forming, ultrasonic cleaning; adopting PIP process to introduce ZrB 2 The ultra-high temperature ceramic phase is impregnated and cracked after 3 cycles. The specific process parameters are: vacuum degree -0.1MPa, immersion pressur...

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Abstract

The invention discloses a laminated C / S-SiC-ZrB2 composite material and a preparation method thereof, belonging to the technical field of ceramic-base composite materials. The composite material is ofa various-component laminated integral structure, and C / C, gradient C / C-SiC, a C / SiC-ZrB2 composite material and an SiC coating layer are sequentially and symmetrically distributed from center to twosides; by virtue of the distribution of carbon and an SiC matrix in the center, the mechanical property is improved, and the density is reduced; and by virtue of the enrichment of ZrB2 on an outer layer, super-high temperature ablation resistance is realized. According to the preparation method, a C / C layer and a C / C-SiC layer can be prepared within 20-40 hours, and a large number of pores are remained in the surface layer of a carbon fiber preform, so that the ZrB2-SiC super-high temperature ceramic can be introduced in a subsequent precursor dipping splitting process. According to the design of the material, the improvement of the comprehensive properties such as dynamics, ablation, oxidation and lightness are adequately considered, and the preparation cycle is greatly shortened; and zero ablation of the material under an electric arc wind tunnel examining material at 2100 DEG C is realized.

Description

Technical field: [0001] The invention relates to the technical field of ceramic matrix composite materials, specifically a laminated structure C / C-SiC-ZrB 2 Composite materials and methods for their preparation. Background technique: [0002] C / C and coatings, C / SiC composite materials have properties such as high temperature resistance, low expansion, high specific strength, low density, and ablation resistance. As thermal protection materials, they are widely used in nose cones, wing leading edges, control rudders, etc. In the thermal protection system of the aircraft. However, as the flight speed of aircraft is getting faster and faster, C / C and coatings, C / SiC can no longer meet the long-term use requirements in ultra-high temperature and aerobic environments, and there is an urgent need to break through long-term thermal protection technology above 1650 °C. [0003] Ultra-high-temperature ceramics (UHTC) generally have a melting point above 3000°C and have excellent a...

Claims

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Application Information

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IPC IPC(8): C04B41/87C04B35/83C04B35/571C04B35/58
CPCC04B35/571C04B35/58078C04B35/83C04B41/009C04B41/5059C04B41/4531
Inventor汤素芳庞生洋胡成龙杨鸷
OwnerINST OF METAL RESEARCH - CHINESE ACAD OF SCI