摘要
固体火箭发动机喷管的烧蚀预示是喷管结构分析的重要一环。本文用有限元法计算了喷管扩张段绝热层的烧蚀，计算中考虑了对流换热、材料热解及烧蚀吸热。计算结果与发动机热试车解剖结果相近。
Ablation prediction of solid rocket motor nozzle is an important link for nozzle structure analysis.In this paper,ablation of a nozzle divergence cone insulation is calculated by the finite element method,considering the convective heat transfer and heat absorption for material thermal decomposition and ablation.The calculation result is similar to the dissected result after the motor test.
出处
《固体火箭技术》
EI
CAS
CSCD
1999年第3期16-19,共4页
Journal of Solid Rocket Technology
