文档介绍：国防科技大学学报
第 31 卷第 2 期 JOURNAL OF NATIONAL UNIVERSITY OF DEFENSE TECHNOLOGY Vol. 31 No. 2 2009
文章编号: 1001- 2486( 2009) 02- 0036- 05
二氧化硅气凝胶隔热复合材料的性能及其瞬态传热模拟X
周祥发1, 2 , 冯坚1, 肖汉宁2 , 张长瑞1 , 姜勇刚1
( 1. 国防科技大学航天与材料工程学院, 湖南长沙 410073; 2. 湖南大学材料科学与工程学院, 湖南长沙 410082)
摘要: 高马赫数、新型航天飞行器承载严重的气动加热环境, 其隔热材料的性能与传热计算对飞行器热
防护结构的优化和预测具有一定的指导意义。研究了二氧化硅气凝胶隔热复合材料的结构与性能, 并进行了
瞬态传热模拟。结果表明复合材料热导率仅为 01018WPm#K, 瞬态传热模拟结果与考核测试值吻合, 为预测和
优化隔热材料提供了一定的依据。
关键词: 隔热; 二氧化硅气凝胶; 热导率; 有限差分法
中图分类号:TQ343 文献标识码: A
Performance and Heat Transfer Simulation of Silica
posites
ZHOU Xiang-fa1, 2 , FENG Jian1 , XIAO Han-ning2 , ZHANG Chang-rui1 , JIANG Yong-gang1
( 1. College of Aerospace and Material Engineering, National Univ. of Defense Technology, Changsha 410073, China;
2. College of Materials and Engineering, Hunan University, Changsha 410082, China)
Abstract: With the development of high-speed spacecrafts, the properties and heat transfer simulation of thermal protection materials
used by the spacecrafts are of great significance. This study aims to study the properties of silica posites and heat transfer
simulation. The results indicate that thermal conductivity of the silica posites is only 0. 018WPm#K and transient heat transfer
simulation shows good agreement with the experimental data. Thus the simulation method can forecast the experimental conclusions and
optimize the geometric st