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针对新型航天飞行器高温隔热(约1 500℃)的迫切需求,开展了超高温刚性隔热材料的制备和性能研究。采用陶瓷纤维和无机粘结剂,经过湿法抽滤成型、高温热处理等工艺制备了刚性隔热材料。对材料的微观结构、热物理和力学性能进行了表征、测试。结果表明:纤维有效粘结在一起;通过改变纤维和粘结剂的比例,可以调节材料性能;热导率、力学性能与密度近似呈直线关系。材料在1 500℃经1 h处理后线收缩率<2%,密度为0.3~0.5 g/cm3,热导率为0.06~0.09 W/(m.K),压缩强度为0.6~1.2 MPa。
In response to the urgent need of high-temperature thermal insulation (about 1 500 ℃) of the new spacecraft, the preparation and performance study of the ultra-high-temperature rigid heat-insulating material has been carried out. Using ceramic fiber and inorganic binder, through wet filtration, heat treatment and other technology to prepare a rigid insulation material. The microstructure, thermophysical and mechanical properties of the materials were characterized and tested. The results show that: the fibers are effectively bonded together; by changing the ratio of fiber and binder, the material properties can be adjusted; the thermal conductivity, mechanical properties and density are approximately linear. After 1 h treatment at 1 500 ℃, the linear shrinkage was less than 2%, the density was 0.3-0.5 g / cm3, the thermal conductivity was 0.06-0.09 W / (m.K), and the compressive strength was 0.6-1.2 MPa.