充气式再入减速系统柔性热防护材料的设计及性能研究  

Design and performance of flexible thermal protection material for inflatable reentry deceleration system

作　　者：曹旭[1,2] 黄明星 黎光宇[1] 孙小飞[3] 黄伟[1] Cao Xu;Huang Mingxing;Li Guangyu;Sun Xiaofei;Huang Wei

机构地区：[1]北京空间机电研究所,北京100094 [2]北京理工大学宇航学院,北京100081 [3]中钢集团洛阳耐火材料研究院有限公司先进耐火材料国家重点实验室,河南洛阳471039

出　　处：《耐火材料》2022年第2期150-153,共4页Refractories

基　　金：载人航天预先研究项目(040101)。

摘　　要：针对充气式再入减速系统再入返回地球过程的热防护需求,在陶瓷纤维布和高强芳纶织物的基础上,使用氧化铝纤维毯、氧化铝复合二氧化硅纤维毯、二氧化硅纤维毯和气凝胶复合玻璃纤维,设计并制备了多层柔性热防护材料。通过热导率测试、静态热冲击试验、动态高焓风洞试验对材料的性能进行了验证。结果表明,所研制的多层柔性热防护材料在动态高焓风洞试验中结构保持完整,具有较好的隔热能力,保证内部承载层的温度在许用范围内,隔热层在试验后性状无明显变化,柔软、可折叠。In view of the thermal protection requirements of the return-to-Earth process of the inflatable reentry deceleration system,on the basis of ceramic fiber cloth and high strength textile,the multilayer flexible thermal protection material was designed and developed using alumina fiber blanket,alumina composite silica fiber blanket,silica fiber blanket composite aerogel composite glass fiber.The performance of the material was verified by the thermal conductivity test,the static thermal shock test and the dynamic high enthalpy wind tunnel test.The results show that the developed multilayer flexible thermal protection material is intact in the dynamic high enthalpy wind tunnel test and has good heat insulation capacity,ensuring that the temperature of the internal bearing layer is within the allowable range.The insulation layer does not change significantly after the test and is still soft and folding.

关 键 词：柔性热防护 氧化铝织物 多层隔热 热冲击 高焓风洞 

分 类 号：TQ175[化学工程—硅酸盐工业]