View in EDS

Ablation behavior of C/SiC-ZrB2 composites prepared via polymer precursor impregnation and pyrolysis in high-enthalpy plasma flows.

Saved in:
Bibliographic Details
Title: Ablation behavior of C/SiC-ZrB2 composites prepared via polymer precursor impregnation and pyrolysis in high-enthalpy plasma flows.
Authors: Zhao, Xing1,2 (AUTHOR), Bai, Yuhang1 (AUTHOR) Yuhang_bai@xust.edu.cn, Yang, Yang1 (AUTHOR), Yao, Zelong1 (AUTHOR), Wu, Yuhao1 (AUTHOR), Liu, Jia1 (AUTHOR), Wang, Zijing1 (AUTHOR), Ren, Ke3 (AUTHOR), Du, Huiling1 (AUTHOR), Song, Yan1,4 (AUTHOR) songyan1211@xjtu.edu.cn
Source: Ceramics International. Oct2025:Part B, Vol. 51 Issue 24, p42089-42098. 10p.
Subjects: Ablative materials, Composite materials, Pyrolysis, Plasma currents, Material erosion, Catalytic activity
Abstract: This study investigates the ablation behavior of polymer precursor impregnation and pyrolysis-derived C/SiC–ZrB 2 composites under high-enthalpy plasma flows. Composites with 60 vol% ZrB 2 and 40 vol% SiC exhibit stable surface temperatures (1760–1815 °C) and low ablation rates R l from −6.67 × 10−5 to −9.67 × 10−4 mm/s, which is attributed to the formation of a cohesive ZrO 2 –SiO 2 oxide layer that mitigates oxygen diffusion and erosion. By contrast, composites with 80 vol% ZrB 2 and 20 vol% SiC are subjected to drastic temperature increases (>2800 °C) under extreme conditions (3.5 MW/m2). Such high ZrB 2 content leads to the formation of numerous ZrO 2 columnar crystals on the surface, which accelerates surface catalytic reactions, thereby increasing the surface temperature. Thermodynamic simulation results reveal that SiC in ZrB 2 –SiC composites is subjected to thermochemical instabilities and atomic oxygen oxidation. These exothermic processes ultimately promote SiC decomposition, ZrO 2 skeleton collapse, and C fiber combustion, leading to the overall composite failure. Achieving the optimal ablation resistance requires a careful balance of ZrB 2 /SiC volume ratio to stabilize the oxide layer while minimizing catalytic effects. These findings contribute to the design of advanced hypersonic thermal protection systems. [ABSTRACT FROM AUTHOR]
Copyright of Ceramics International is the property of Elsevier B.V. and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)
Database: Engineering Source
Description
Abstract:This study investigates the ablation behavior of polymer precursor impregnation and pyrolysis-derived C/SiC–ZrB 2 composites under high-enthalpy plasma flows. Composites with 60 vol% ZrB 2 and 40 vol% SiC exhibit stable surface temperatures (1760–1815 °C) and low ablation rates R l from −6.67 × 10−5 to −9.67 × 10−4 mm/s, which is attributed to the formation of a cohesive ZrO 2 –SiO 2 oxide layer that mitigates oxygen diffusion and erosion. By contrast, composites with 80 vol% ZrB 2 and 20 vol% SiC are subjected to drastic temperature increases (>2800 °C) under extreme conditions (3.5 MW/m2). Such high ZrB 2 content leads to the formation of numerous ZrO 2 columnar crystals on the surface, which accelerates surface catalytic reactions, thereby increasing the surface temperature. Thermodynamic simulation results reveal that SiC in ZrB 2 –SiC composites is subjected to thermochemical instabilities and atomic oxygen oxidation. These exothermic processes ultimately promote SiC decomposition, ZrO 2 skeleton collapse, and C fiber combustion, leading to the overall composite failure. Achieving the optimal ablation resistance requires a careful balance of ZrB 2 /SiC volume ratio to stabilize the oxide layer while minimizing catalytic effects. These findings contribute to the design of advanced hypersonic thermal protection systems. [ABSTRACT FROM AUTHOR]
ISSN:02728842
DOI:10.1016/j.ceramint.2025.06.424