| 某固体火箭发动机热结构的ANSYS有限元分析 |
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| 引用本文： | 张斌兴.某固体火箭发动机热结构的ANSYS有限元分析[J].上海航天,2007,24(5):62-64. |
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| 作者姓名： | 张斌兴 |
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| 作者单位： | 中国人民解放军海军驻上海地区航天系统军代室,上海,200235 |
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| 摘 要： | 基于ANSYS软件对某固体火箭发动机(SRM)的热结构进行了有限元分析。计算了潜入式喷管瞬态温度场和应力场,用间接耦合解法进行热-应力耦合分析。结果表明:计算值与实测结果较吻合,可为SRM的热结构分析提供一种实用快捷的计算方法。
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| 关 键 词： | 固体火箭发动机 热结构 温度场 应力场 有限元法 |
| 文章编号： | 1006-1630（2007）05-0062-03 |
| 收稿时间： | 2007-03-06 |
| 修稿时间： | 2007-04-11 |
Finite Element Analysis of Some SRM Thermo-Structure Based on ANSYS Software |
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| ZHANG Bin-xing.Finite Element Analysis of Some SRM Thermo-Structure Based on ANSYS Software[J].Aerospace Shanghai,2007,24(5):62-64. |
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| Authors: | ZHANG Bin-xing |
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| Abstract: | The finite element analysis of the thermo-structure for some solid rocket motor(SRM) based on ANSYS software was discussed in this paper.The transient temperature field and stress field of the submerged nozzle in a SRM were calculated,and the thermo-structure was analyzed by indirect coupling method.The analysis results showed that the computation values were basically identical with tested results.The method could provide a useful and convenient method for SRM thermo-structure analysis. |
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| Keywords: | Solid rocket motor Thermo-structure Temperatute field Stress field Finite element method |
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