航天器环境工程Issue(5)：516-521,6.DOI:10.3969/j.issn.1673-1379.2013.05.012
高超声速飞行器热防护结构参数优化及对比分析
The optimization and comparison of thermal protection structures for hypersonic aircraft
摘要
Abstract
Hypersonic aircraft requires a good structural performance, good thermal protection properties and the lightest weight. To minimize the weight, an optimization of the thermal structure is made by establishing a one-dimensional thermal transfer model under different thermal conditions, using the aluminum alloy or advanced composite materials as the skin. This paper analyzes the effects of the heat load, the re-entry time, and the skin materials on the TPS weight. Through optimizing the dimensions of the thermal structure, the minimum TPS weight per unit area is calculated. ANSYS simulation results show that the temperature has a prominent effect on the minimum TPS weight per unit area;LI900 and AMHC have an advantage over other TPS concepts;Composite material skin may help reduce the TPS weight. The initial re-entry temperature and the re-entry time have a more significant effect on the rigid ceramic tiles than on the metallic cover insulation.关键词
高超声速飞行器/热防护结构/设计优化/重量控制/仿真分析Key words
hypersonic aircraft/thermal protection structure/design optimization/weight control/simulation analysis分类
航空航天引用本文复制引用
叶红,王志瑾..高超声速飞行器热防护结构参数优化及对比分析[J].航天器环境工程,2013,(5):516-521,6.基金项目
江苏省高校优势学科建设资助项目 （）
