Excellent ablation resistance and reusability of silicon carbide fiber reinforced silicon carbide composite in dissociated air plasmas |
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| Affiliation: | 1. Key Laboratory for Wind and Bridge Engineering, Hunan University, Changsha, China;2. College of Civil Engineering, Hunan University, Changsha, China;3. Department of Civil, Environmental and Geomatic Engineering, University College London, United Kingdom;4. Department of Mechanical Engineering, University College London, United Kingdom;1. IMRI, University of Bolton, Deane Road, Bolton BL3 5AB, UK;2. LNE, CARMEN Platform, DMSI, 29 Avenue Roger Hennequin, 78197 Trappes, France;3. PCH, IMT Mines Ales, 6 Avenue de Clavières 30319 Alès Cedex, France;4. Dstl, Porton Down, Salisbury SP4 0JQ, UK;1. Department of Mechanical Engineering, The University of Hong Kong, Hong Kong, China;2. Department of Building Environment and Energy Engineering, The Hong Kong Polytechnic University, Hong Kong, China;3. Department of Mechanical Engineering, The Hong Kong Polytechnic University, Hong Kong, China;1. MATIM, University of Reims Champagne-Ardenne, France;2. Pôle de Recherche Châlonnais, University of Reims Champagne-Ardenne, France |
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| Abstract: | This work explores the potentials of SiC fiber reinforced SiC matrix composites (SiCf/SiC) with SiC coating to resist aerodynamic ablations for thermal protection purpose. A plasma wind tunnel is employed to evaluate their anti-ablation property in dissociated air plasmas. The results suggest a critical ablation temperature of SiC coated SiCf/SiC, ≈ 1910 °C, which is the highest ever reported in literatures. Benefited by ‘all-SiC’ microstructures and relative flat ablated surfaces, the SiCf/SiC is still ablation-resistant up to ≈ 1820 °C after the occurrence of ablation. This implies an excellent ablation resistance and reusability property of SiCf/SiC, which surpasses that of traditional carbon fiber reinforced composites. Finally, an ablation mechanism dominated by surface characteristic is proposed. For the SiC coated SiCf/SiC, ablation is prone to take place at surface cracks formed by thermal mismatch; while for the ablated SiCf/SiC, ablation is triggered at the exposed fiber bundles which is over-heated in the plasmas. |
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| Keywords: | Space vehicle Thermal protection system Ceramic matrix composite Silicon carbide Ablation mechanism |
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