用有限元法计算边界移动的喷管温度场  

A CALCULATION ABOUT A TEMPERATURE FIELD OF BOUNDARY MOVEMENT NOZZLE WITH FINITE ELEMENT METHODE

作　　者：孙冰[1] 孙菊芳[1] 

机构地区：[1]北京航空航天大学宇航学院

出　　处：《推进技术》1995年第5期54-58,共5页Journal of Propulsion Technology

摘　　要：以固体火箭发动机复合结构喷管为对象，用有限元法进行了二维轴对称瞬态热分析。计算中考虑了因烧蚀引起的边界移动．且实现了网格的自适应，给出了考虑与不考虑烧蚀情况下的温度场计算结果，并将计算结果与试验结果做了比较，二者吻合较好，说明该预估方法既具有理论意义又有实用价值。two-dimensional axisymmetric transient thermal analysis for a composite construction nozzle of solid rocket motor is performed by finite element method in this paper. Boundary movement caused by ablation is achieved in the calculation. The calculative results agree well with the experimental results, which shows that the predicting method in this paper has theoretical value as wall as practical worth.

关 键 词：火箭发动机 喷管 温度分布 烧蚀 固体推进剂 

分 类 号：V435.14[航空宇航科学与技术—航空宇航推进理论与工程] V435.23