防隔热一体化TPS材料制备及耐高温性能

Preparation and high temperature resistance property of TPS material with integrated thermal insulation

为满足高速飞行器大面积热防护(≥1500℃)需求,以耐高温氧化铝纤维增强气凝胶复合材料作为隔热层,碳纤维织物为面板层预制体,通过法向针刺穿刺工艺以及先驱体浸渍裂解工艺,制备防隔热一体化TPS材料,并开展耐高温性能测试研究,为材料的工程化应用提供理论与技术支持。结果表明:采用针刺穿刺缝合技术与PIP工艺可以制备防隔热一体化TPS材料,整体性较好,无明显的缺陷,密度仅为0.6 g/cm^(3)。C/SiC复合材料在高温氧化环境中使用,氧化性气氛通过孔隙与裂纹等缺陷扩散进入材料内部,与碳纤维发生氧化反应,导致复合材料性能的下降。材料具有优异的耐高温性能,材料的质量烧蚀率为0.051 g/s,线烧蚀率为0.077 mm/s;未出现显著的间隙结构,整体无明显收缩,呈现出较好的耐高温性能。

In order to meet the needs of large area thermal protection(≥1500℃)for high-speed aircraft,the high temperature resistant alumina fiber reinforced aerogel composite was used as the thermal insulation layer,and the carbon fiber fabric was used as the panel layer preform.Through the normal needle puncture process and the precursor impregnation pyrolysis process,the integrated TPS material for thermal protection was prepared,and the high temperature resistance performance tests were carried out to provide theoretical and technical support for the engineering application of materials.The results show that the integrated TPS material with good integrity and no obvious defects can be prepared by needle puncture suture technology and PIP process,and the density is only 0.6 g/cm^(3).When C/SiC composites are used in high-temperature oxidation environment,the oxidizing atmosphere diffuses into the material through defects such as pores and cracks,and oxidizes with carbon fibers,resulting in the degradation of composite properties.The material has excellent high temperature resistance,with mass ablation rate of 0.051 g/s and linear ablation rate of 0.077 mm/s;There is no obvious gap structure,and there is no obvious shrinkage on the whole,showing good high temperature resistance.