高硅氧增强塑料烧蚀模型中热解层厚度的探讨

A DISCUSSION ON THE THICKNESS OF PYROLYSIS LAYER IN THE ABIATION MODEL FOR SILICAPHENOLICS COMPOSITE MATERIAL

关键词:  火箭发动机喷管  烧蚀  模型  玻璃纤维增强塑料  固体火箭发动机

Key words:  Rocket engine nozzle  Ablation  Model  Class fiber reinforced plastic  Solid rocket engine

摘要:

通过小型实验固体火箭发动机的多次热试车,对喷管扩散段截面上高硅氧酚醛材料的色变厚度进行了观察,对该截面上材料采用红外光谱成份分析和导电性测量,确认了热解层厚度与碳化层厚度具有相同的数量级,可达2.5mm左右.因此,在作高硅氧酚醛喷管材料的烧蚀与温度场计算时,不宜采用热解面模型,而应采用热解层模型.

Abstract:

By means of the firing tests of a small experimental solid: rocket motor, o-bserving colour change of the silica-phenolics composite material on the divergent section of the nozzle, and also using infrared ray spectral analysis and condu-ctimetry for the meter ill coundl the she chickness of pyroly-sis layer is of the same order of magnitude as the thickness of charring layer, which is up to 2.5mm. For this reason, It is concluded that the pyrolysis layer model,rather than the pyrolysis surfacc model should be adopted to calculate of theablation rate and the temperature distribution of the silica-phenolies composite no-zzle.