关键词: 固体火箭发动机;喷管喉部;喷管烧蚀计算;碳酚醛材料

Abstract: The ablation mechanism and the performance of carbon-phenolic material of solid propellant rocket nozzles are studied. The influences of chemical reactions, particle impingement and the shear stresses in boundary layers on the recession process are also analysed and calculated in this paper.Based on the comparison of experimental results with the predicted ones, an empirical correlation to predict the total recession including both chemical and mechanical effects is developed.

Key words: Solid propellant rocket;Nozzle throat;Nozzle ablation calculation;Carbon-phenolic material