摘要
文中基于旋转条件下长尾喷管发动机三维两相流场计算结果,通过提取烧蚀边界参数,分析了该条件下的绝热层烧蚀机理,建立了二维炭化烧蚀模型。开展了不同颗粒直径和旋转速度条件下的绝热层烧蚀预示。计算结果表明旋转条件下烧蚀部位发生显著变化,且烧蚀率随旋转速度的增加而增大;后封头部位的烧蚀主要是由旋转引起的颗粒冲刷主导。
Based on numerical simulation results of three-dimensional two-phase flow field of tail-pipe SRM under spinning condition and the extracted ablation boundary parameter, the two-dimensional charring ablation model under spinning condition was estab lished through analyzing the ablation＇mechanism of insulator. The ablation prediction with different particle diameter and spinning rate was studied. The results show that the ablation position changes evidently under spinning condition and the ablation ratio is enhanced with increasing spinning rate. The insulator ablation in aft closure is caused by highly concentrated particle eroding by spinning.
出处
《弹箭与制导学报》
CSCD
北大核心
2011年第3期138-141,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
基金
国家自然科学基金(50776073)资助
关键词
固体火箭发动机
长尾喷管
两相流
烧蚀
旋转条件
solid rocket motor
tail-pipe nozzle
two-phase flow
ablation
spinning condition
作者简介
作者简介：严聪（1962-），女，福建福州人，副教授，博士研究生，研究方向：航空宇航推进理论与工程。
