| 高超声速飞行器热防护系统尺寸优化设计 |
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| 引用本文： | 徐超,张铎.高超声速飞行器热防护系统尺寸优化设计[J].中国空间科学技术,2007,27(1):65-69. |
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| 作者姓名： | 徐超 张铎 |
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| 作者单位： | 西北工业大学,西安710072 |
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| 摘 要： | 以热防护系统厚度方向几何尺寸为设计变量,热防护结构质量为优化目标函数,以航天器主结构温度极值为约束条件建立了优化模型。采用外部调用NASTRAN进行非线性瞬态有限元热分析,应用复合形法作为优化工具进行全局寻优。针对该问题结构几何形状是变量的特点,采用文件接口的方法实现了设计变量与有限元模型的关联以及有限元分析结果与优化工具的数据交换。
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| 关 键 词： | 防热结构 尺寸 最优设计 航天器 |
| 修稿时间： | 2005-06-23 |
Size Optimization of Thermal Protection Systems for Hypersonic Aircraft |
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| Xu Chao,Zhang Duo.Size Optimization of Thermal Protection Systems for Hypersonic Aircraft[J].Chinese Space Science and Technology,2007,27(1):65-69. |
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| Authors: | Xu Chao Zhang Duo |
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| Abstract: | An engineering method for sizing the thermal protection system(TPS) of hypersonic vehicles was built.Complex optimization method was used to seek optimal thickness with the aim to minimize the TPS weight and limit the aircraft main-structure temperature under acceptable bound.A general purpose finite element(FE) analysis tool NASTRAN was used to get time-variable temperature field at given TPS size.An interface code was created to relate and combine the FE thermal analysis and optimization solving.Details of data exchange between them are present.Finally a numerical example was given and optimization results were discussed detailed. |
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| Keywords: | Heat-protection construction Dimension Optimum design Spacecraft |
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