摘要
通过设定红外加热笼与卫星表面之间不同距离,改变加热笼的覆盖系数,仿真模拟了卫星表面到达热流的分布,研究了加热笼的覆盖系数对卫星表面到达热流密度均匀性的影响,分析结果表明:当加热笼距离卫星表面100mm以上,选取覆盖系数大于0.06的加热笼,即可满足到达卫星表面热流的均匀性要求。
The distribution of flux on spacecraft surface is simulated by setting, different distances between infrared heating cage and spacecraft surface ＆ changing the coverage coefficient of infrared heating cage. Moreover, the effect of flux uniformity on spacecraft surface is analyzed resulting from cover coefficient of infrared heating cage. The results indicate that when the distance between infrared heating cage and spacecraft surface is more than 100mm, it can be met the equirement of flux uniformity on spacecraft surface if the selected coverage coefficient of infrared heating cage is higher than 0. 06.
出处
《航天器工程》
2008年第5期38-41,共4页
Spacecraft Engineering
关键词
卫星
真空
热试验
红外加热笼
覆盖系数
热流均匀性
spacecraft
vacuum
heating tests
infrared heating cage
cover coefficient
flux uniformity
