| 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。 |
| 关键词: 火箭发动机喷管 温度分布 有限元法 浇蚀 |
| DOI： |
| 分类号:V430 |
| 基金项目: |
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| A CALCULATION ABOUT A TEMPERATURE FIELD OF BOUNDARY MOVEMENT NOZZLE WITH FINITE ELEMENT METHODE |
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Sun Bing, Sun Jufang
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School of Astronautics, Beliing Univ. of Aeronautics and Astronautics, Beijing, 100083
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| Abstract: |
| 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. |
| Key words: Rocket nozzle Temperature distribution Finite element method Ablation |
