摘要
航天运载器在高速飞行时所经受的气动热环境十分严酷,然而由于应用的要求,在其结构上不得不安排一些突起物和缝隙等局部结构,它们会干扰周围的流场,使其局部热环境异常严酷—"局部过热"。根据高气动加热环境下引发"局部过热"问题为背景,提出利用电弧加热器湍流平板试验手段进行防热材料筛选试验,根据运载器局部结构特点进行针对性防热设计,通过电弧风洞热试验技术考核防热层性能、验证局部防热设计方案的正确性,为热防护结构设计提供支撑。
As a launch vehicle for hypersonic flight, some topical structure has to be designed, which results in a greater aerodynamic beating. This paper presents a notion coupled TPS design with testing. By means of material selection, TPS design and heat testing, the design is justified.
出处
《强度与环境》
2016年第1期54-59,共6页
Structure & Environment Engineering
关键词
气动加热
运载器
热防护
试验研究
aerodynamic heating
launch vehicle
thermal protection
study on testing
