充气式再入与减速系统用柔性热防护材料高焓风洞试验研究  

High enthalpy wind tunnel test of flexible thermal protection system for inflatable reentry and descent vehicle

作　　者：曹旭[1,2] 黄明星 CAO Xu;HUANG Mingxing(Beijing Institute of Space Mechanics and Electricity,Beijing 100094,China;School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China)

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

出　　处：《航天器环境工程》2020年第2期184-190,共7页Spacecraft Environment Engineering

基　　金：载人航天预先研究项目(编号:040101).

摘　　要：为考察充气式再入与减速系统用柔性热防护材料的真实性能,文章根据前期的技术基础和各材料的技术参数,确定了柔性热防护材料的结构组成,并研制了热防护材料试验件进行高焓风洞试验。结果表明:所研制的材料能够承受热流密度为25 W/cm^2、持续时间最长达300 s的高温环境;Nextel氧化铝织物作为防热层在超过1200℃下能够有效阻隔热流;无机隔热毡起到了有效的隔热作用,可确保内部Kevlar织物处于250℃以下的环境中。材料满足一定的轻量化要求,试验后整体力学性能稳定,热防护性能不受折叠和缝纫工艺影响。To investigate the properties of flexible thermal protection materials used for the inflatable reentry and descent system, the TPS materials are designed according to the previous work and the technical parameters of such kind of materials, and several test samples are developed for the high enthalpy wind tunnel test study. Test results show that the test samples can withstand a thermal flux up to 25 W/cm^2 for 300 s, in that the Nextel alumina textile plays the role of the effective insulation for temperature over 1200 ℃, and the inorganic insulation layer has very low thermal conductivity: those two layers could effectively bring down the temperature of the Kevlar textile to one lower than 250 ℃. The material can meet the light weight requirement to a certain extent, with its mechanical properties remaining generally stable after the test, and its thermal protection property insusceptible to the folding process and the sewing process.

关 键 词：充气式再入与减速 柔性热防护材料 高焓风洞试验 氧化铝层 温度测量 热电偶 

分 类 号：V475.9[航空宇航科学与技术—飞行器设计]