材料科学
热膨胀
复合数
复合材料
各向异性
陶瓷
变形(气象学)
弯曲
热的
航天飞机热防护系统
等温过程
烧焦
热保护
热解
化学工程
物理
热力学
量子力学
气象学
工程类
作者
Xiaofeng Chi,Zhengguang Heng,Liwei Yan,Yang Chen,Yuanbo Cai,Chuan Zhou,Huawei Zou,Mei Liang
标识
DOI:10.1021/acsami.4c06355
摘要
Rigid thermal protection materials such as ultra-high-temperature ceramics are desirable for applications in aerospace vehicles, but few materials can currently satisfy the emerging high-temperature sealing requirements for dynamic gaps created by the mismatch of the thermal expansion of different protection layers. Here, we design and fabricate a flexible biomimetic anisotropic deformation composite by multilayer cocuring onto fiber fabrics. It displays superior anisotropic deformation, whose longitudinal expansion ratio is 48 times greater than the transverse expansion ratio at specific temperatures. Furthermore, the ordered carbon structure created by transition-metal-catalyzed graphitization and the C/Si synergistic effect resulting from the combination of biomimetic fiber fabrics and SR enable the in situ formation of a high-temperature-resistant SiC crystalline phase within the char layer, ultimately resulting in exceptional thermal protection properties. By constructing hollow structures in situ, the back temperature of the composite, which is only 4.33 mm thick, is stabilized at 140 °C under the condition of continuous butane flame ablation (1300 °C) for 420 s. Multilayer structure and flexible features can facilitate large-scale preparation and arbitrary cutting and bending, adapted to different thermal protection areas.
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