| 航天飞行器防热部件烧蚀行为的数值模拟 |
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| 引用本文： | 吕德生,宋桂明,周玉,王玉金,贾德昌,段小明.航天飞行器防热部件烧蚀行为的数值模拟[J].固体火箭技术,2002,25(2):67-69. |
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| 作者姓名： | 吕德生 宋桂明 周玉 王玉金 贾德昌 段小明 |
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| 作者单位： | 哈尔滨工业大学材料学院,哈尔滨,150001 |
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| 摘 要： | 对航天飞行器防热部件在氧－煤油发动机火焰喷吹下的烧蚀行为进行了有限元数值模拟。利用“杀死”单元的方法建立防热部件瞬态温度场的有限元模型，实现了烧蚀边界的退缩，从而完成了对烧蚀尺寸变化的定量描述。烧蚀开始于4．59s，到12s时线烧蚀量为1．47mm。计算结果与试验的实测结果一致。
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| 关 键 词： | 航天飞行器 防热部件 烧蚀行为 数值模拟 线烧蚀率 防热材料 |
| 文章编号： | 1006-2793(2002)02-0067-03 |
| 修稿时间： | 2001年9月27日 |
Numerical simulation of ablation behavior of spacecraft thermo-resistance components |
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| LU De-sheng,SONG Gui-ming,ZHOU Yu,WANG Yu-jin,JIA De-chang,DUAN Xiao-mingSchool of Material Science and Engineering,Harbin Institute of Technology,Harbin ,China..Numerical simulation of ablation behavior of spacecraft thermo-resistance components[J].Journal of Solid Rocket Technology,2002,25(2):67-69. |
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| Authors: | LU De-sheng SONG Gui-ming ZHOU Yu WANG Yu-jin JIA De-chang DUAN Xiao-mingSchool of Material Science and Engineering Harbin Institute of Technology Harbin China |
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| Institution: | LU De-sheng,SONG Gui-ming,ZHOU Yu,WANG Yu-jin,JIA De-chang,DUAN Xiao-mingSchool of Material Science and Engineering,Harbin Institute of Technology,Harbin 150001,China. |
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| Abstract: | The ablation behavior of spacecraft thermo-resistance components under blowing by oxygen-kerosene flame is investigated by means of finite element numerical simulation.The method of element death is used to develop a finite element model of the transient temperature field in the component, which is suitable for dealing with the recede of the ablation boundary, thereby, the ablation behavior can be quantitatively described. The regression of the ablation boundary is initiated at 4.59s, and the ablation thickness is 1.47mm at 12s.The calculations are consistent with the results. |
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| Keywords: | linear ablation rate temperature field numerical simulation |
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