摘要
介绍了固体火箭冲压发动机EPDM绝热层的烧蚀过程及模型,在忽略粒子侵蚀和机械剥蚀的基础上,分析了EPDM炭化层表面的主要热化学烧蚀反应及烧蚀产物的确定方法,提出了炭化层烧蚀率的粗略预示方法,对EPDM绝热层的热化学烧蚀机理进行了初步探索。
The EPDM insulator＇s ablating processes and some models for the solid ducted rocket motor are introduced simply and the main thermochemistry reactions on the insulator＇s surface and ablation products are analyzed based on the omitting of particle collision and mechanical impact.Approximating prediction of charring layer ablating was presented and the preliminary exploring of the thermochemical ablation mechanism of EPDM insulator was conducted.
出处
《宇航材料工艺》
CAS
CSCD
北大核心
2010年第5期15-17,共3页
Aerospace Materials & Technology
