固体火箭技术2011，Vol.34Issue(2)：189-192,201,5.
长时间工作固体火箭发动机燃烧室热防护层烧蚀计算
Computation of ablation of thermal-protection layer in long-time working solid rocket motors
摘要
Abstract
In order to study thermal-protection function of long-time working solid rocket motors, insulation ablation and temperature field of long-time working solid rocket motors were coupling calculated by moving boundary explicit-difference method and three equations ablation model. Ablation velocity caused by chemical reaction or diffnsion process and temperature of inner wall were calculated. Numerical results show that the ablation is restricted by the diffusion process. In addition, when solving the ablation subroutine,a convenient and effective method for setting initial value was proposed. Using this new method, the reasonable results were obtained and the calculation time was greatly decreased. This research can offer an effective analytical method for long-time working solid rocket motors.关键词
固体火箭发动机/内绝热层/烧蚀/初值Key words
solid rocket motor/ internal insulation layer/ ablation/ initial value分类
航空航天引用本文复制引用
张斌,刘宇,王长辉,任军学..长时间工作固体火箭发动机燃烧室热防护层烧蚀计算[J].固体火箭技术,2011,34(2):189-192,201,5.基金项目
"863"国家高技术研究发展计划(2007AA702311、2008AA7020508). （2007AA702311、2008AA7020508）
