摘要
本文采用有限差分法及有限元素法计算了航天飞机防热结构的一、二维温度分布,并与飞行实测数据及实验结果进行了比较,符合较好。
In the paper the finite difference method and the finite element method have been used to determine the temperature distribution through the multilayer isulative systems of the space shuttle. The computed results have been compared with the STS-2 flight data and other experimental results; they show good agreements.
出处
《空气动力学学报》
CSCD
北大核心
1992年第3期367-372,共6页
Acta Aerodynamica Sinica
关键词
航天飞机
热防护系统
数值计算
space shuttle, TPS, numerical method, heat-conduction equation.
