耐烧蚀超高温陶瓷改性C/C复合材料的研究进展
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摘要
炭/炭(C/C)复合材料在高温含氧环境中易氧化烧蚀的问题影响了其在航空航天领域的应用,引入超高温陶瓷能有效地提高其超高温耐烧蚀性能。介绍和分析了化学气相渗透、先驱体浸渍裂解、反应熔渗等基体改性工艺及其优缺点;综述了近年来C/C复合材料基体改性提高其超高温抗烧蚀性能的最新研究进展;并评述了国内在提高C/C复合材料超高温抗烧蚀性能方面取得的一些成果;最后,提出了提高C/C复合材料超高温长时抗烧蚀性能的潜在发展方向。
The shortcoming of easy oxidation for carbon/carbon(C/C) composites in oxidizing environments has limited the applications of C/C composites in aerospace field. Adding ultra-high temperature ceramics(UHTCs) to C/C composites can improve their ablation resistance. The technologies for matrix modification, including chemical vapor infiltration, precursor infiltration pyrolysis, reactive melt infiltration, and the advantages and disadvantages of these technologies were introduced and analyzed. Recent progress on anti-ablation properties for C/C composites at ultra-high temperature was reviewed. Some results about the anti-ablation property of C/C composites were also summarized. Finally, the potential development direction of improving long-time ablation resistance for C/C composites was proposed.
The shortcoming of easy oxidation for carbon/carbon(C/C) composites in oxidizing environments has limited the applications of C/C composites in aerospace field. Adding ultra-high temperature ceramics(UHTCs) to C/C composites can improve their ablation resistance. The technologies for matrix modification, including chemical vapor infiltration, precursor infiltration pyrolysis, reactive melt infiltration, and the advantages and disadvantages of these technologies were introduced and analyzed. Recent progress on anti-ablation properties for C/C composites at ultra-high temperature was reviewed. Some results about the anti-ablation property of C/C composites were also summarized. Finally, the potential development direction of improving long-time ablation resistance for C/C composites was proposed.
引文
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