Comparison of the ablation resistance of mullite modified C/C-SiC-HfC and C/C-SiC-HfC composites under oxyacetylene flame of 2.38 MW/m2 heat flux

Jiao, Xiaoyang; He, Qinchuan; Feng, Jie; Tan, Qing; Wang, Yiqun; Yin, Xuemin

doi:10.1016/j.ceramint.2023.08.341

Cited by 8 publications

(1 citation statement)

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“…Factors affecting the temperature of the back-face are mainly the ablation surface temperature, thermal conductivity, thermal blocking effect, and thickness of the heat insulation layer. [32,33] Among them, although the ablation surface temperature and residual carbon rate of PR gradually increase with the content of HMTA, the thermal conductivity is close and the thickness of the insulation layer is the same. Hence, the difference in the back-face temperature of these samples were not significant under the combined effect of various factors.…”

Section: Resultsmentioning

confidence: 99%

Yttrium Silicate‐Coated Carbon Fiber Reinforced Phenolic Aerogel‐like Composites with Low Density and Low Ablation

Sun,

Wang,

Huang

et al. 2024

ChemistrySelect

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The evolution of hypersonic vehicles has raised higher requirements for thermal protection materials, which have become the focus of research on how to meet the lightweight and less ablative. Herein, a yttrium silicate‐coated carbon fiber felts (YS‐CFs) reinforced phenolic aerogel‐like (PR) composites were prepared. The YS‐CFs/PR with the addition of 12 % hexamethylenetetramine exhibited low density (0.540 g/cm3), low thermal conductivity (0.145 W/(m⋅K)), and good thermal stability. Specifically, under an oxyacetylene flame examination with 2.44 MW/m2 heated for 120 s, its mass ablation rates (9.833 mg/s) and line ablation rates (5 μm/s) were decreased by 40.8 % and 32.6 %, respectively, compared to others. The results show that the composites with these combined properties can meet the requirements for thermal protection materials in the field of hypersonic vehicles.

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Section: Resultsmentioning

confidence: 99%