低气压环境火箭底部柔性防热材料隔热试验研究  

Experimental Research of Thermal-Insulation Performance of Flexible Thermal Protection Material of Rocket in Low-Pressure Environment

作　　者：薛宇轩 何西波[1] 胡由宏[1] 尹晓峰[1] 沈丹 XUE Yu-xuan;HE Xi-bo;HU You-hong;YIN Xiao-Feng;SHEN Dan(Beijing Institute of Structure and Environment Engineering,Beijing 100076,China;Beijing Institute of Astronautical Systems Engineering,Beijing 100076,China)

机构地区：[1]北京强度环境研究所,北京100076 [2]北京宇航系统工程研究所,北京100076

出　　处：《强度与环境》2021年第2期45-50,共6页Structure & Environment Engineering

摘　　要：文章针对飞行环境的压力变化,采用低气压环境复合瞬态热试验系统,在常压、20kPa、2kPa三种压力环境下模拟了火箭底部柔性防热材料在飞行过程中的瞬态热载荷。通过测试试件升温状态及表面烧蚀状态,研究压力环境对材料隔热性能的影响。通过试验结果对比分析,发现箭体底部柔性防热材料的升温幅度与烧蚀程度均随环境压力的下降而降低,20kPa、2kPa状态下的烧蚀量分别为常压状态下的87%和56%。In this paper,aimed at pressure-change during flight,by use of low pressure-environment composite transient thermal-experiment system,the transient thermal load of flexible thermal protection material used at the bottom of rocket was simulated under normal pressure,20kPa and 2kPa respectively.The effect of environmental-pressure on material’s thermal-insulation performance was discussed by testing structure’s temperature rise and ablation property.The test results show that the temperature rise and degree of ablation of flexible thermal protection material used at the bottom of rocket are all decreasing with the drop of environmental-pressure and that the ablation amount at 20kPa pressure and 2kPa pressure is respectively 87%and 56%of ablation amount at normal pressure.

关 键 词：低气压 柔性防热材料 隔热性能 试验研究 

分 类 号：V416.5[航空宇航科学与技术—航空宇航推进理论与工程]