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Silicon nitride fiber reinforced ceramic matrix composite material and preparation method thereof
The invention belongs to the technical field of structure-function integrated ceramic matrix composite materials, and particularly relates to a silicon nitride fiber reinforced ceramic matrix composite material and a preparation method thereof. The composite material is composed of silicon nitride fibers, a quartz-based matrix and an interface coating between the fibers and the matrix, the quartz-based matrix comprises silicon oxide, aluminum oxide and boric oxide, and the silicon oxide, the aluminum oxide and the boric acid are mixed according to the mass ratio of 70%-90%: 23%-8%: 2%-7%, and the interface coating is one or a combination of two of a silicon-aluminum-oxygen coating and a silicon-nitrogen-oxygen coating. Therefore, the high-temperature mechanical property retention rate of the composite material is further improved. The composite material is resistant to high temperature, high in reliability and capable of being repeatedly used under the high-Mach flight condition, and the use requirement of an antenna window material of a near space hypersonic flight vehicle is met.
本发明属于结构‑功能一体化陶瓷基复合材料技术领域，特别是涉及到一种氮化硅纤维增强陶瓷基复合材料及其制备方法。复合材料由三部分组成分别为：氮化硅纤维、石英基基体和纤维与基体间界面涂层组成，石英基基体成分为氧化硅、氧化铝和氧化硼，按照氧化硅:氧化铝:硼酸的质量比为70％～90％:23％～8％:2％～7％的配比混合，界面涂层为硅‑铝‑氧涂层和硅‑氮‑氧涂层其中一种或两种的组合。从而进一步提高复合材料的高温力学性能保留率。实现在高马赫飞行条件下对复合材料耐高温、高可靠、可重复使用的目标，满足临近空间高超声速飞行器的天线窗口材料的使用要求。
Silicon nitride fiber reinforced ceramic matrix composite material and preparation method thereof
The invention belongs to the technical field of structure-function integrated ceramic matrix composite materials, and particularly relates to a silicon nitride fiber reinforced ceramic matrix composite material and a preparation method thereof. The composite material is composed of silicon nitride fibers, a quartz-based matrix and an interface coating between the fibers and the matrix, the quartz-based matrix comprises silicon oxide, aluminum oxide and boric oxide, and the silicon oxide, the aluminum oxide and the boric acid are mixed according to the mass ratio of 70%-90%: 23%-8%: 2%-7%, and the interface coating is one or a combination of two of a silicon-aluminum-oxygen coating and a silicon-nitrogen-oxygen coating. Therefore, the high-temperature mechanical property retention rate of the composite material is further improved. The composite material is resistant to high temperature, high in reliability and capable of being repeatedly used under the high-Mach flight condition, and the use requirement of an antenna window material of a near space hypersonic flight vehicle is met.
本发明属于结构‑功能一体化陶瓷基复合材料技术领域，特别是涉及到一种氮化硅纤维增强陶瓷基复合材料及其制备方法。复合材料由三部分组成分别为：氮化硅纤维、石英基基体和纤维与基体间界面涂层组成，石英基基体成分为氧化硅、氧化铝和氧化硼，按照氧化硅:氧化铝:硼酸的质量比为70％～90％:23％～8％:2％～7％的配比混合，界面涂层为硅‑铝‑氧涂层和硅‑氮‑氧涂层其中一种或两种的组合。从而进一步提高复合材料的高温力学性能保留率。实现在高马赫飞行条件下对复合材料耐高温、高可靠、可重复使用的目标，满足临近空间高超声速飞行器的天线窗口材料的使用要求。
Silicon nitride fiber reinforced ceramic matrix composite material and preparation method thereof
一种氮化硅纤维增强陶瓷基复合材料及其制备方法
ZHANG SHUWEI (author) / MEN WEIWEI (author) / SU TAO (author)
2021-11-26
Patent
Electronic Resource
Chinese
IPC:
C04B
Kalk
,
LIME
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