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。
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.
出处
《中国空间科学技术》
EI
CSCD
北大核心
2007年第1期65-69,共5页
Chinese Space Science and Technology
关键词
防热结构
尺寸
最优设计
航天器
Heat-protection construction Dimension Optimum design Spacecraft
