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

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.

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