摘要
在航天器热平衡方程的基础上,分析了表面涂层材料热辐射性质或布局调整对内热源变化和轨道变化的适应能力,并对若干情形进行了定量分析。研究表明,该方法有利于继承和保持成熟的航天器平台技术,提高了对不同类型轨道的航天器热设计的灵活性。
The adjustment of thermal radioactive property or distribution of surface coating materials could be applied to spacecraft thermal design.Their adaptive ability for variation of spacecraft internal heat source or orbit is analyzed based on the thermal equilibrium equation.These methods are beneficial to carry on previous platform technology,simultaneously,increase the flexibility of spacecraft thermal design.
出处
《红外技术》
CSCD
北大核心
2011年第5期305-308,共4页
Infrared Technology
关键词
热控涂层
热设计
航天器
thermal control coating
thermal design
spacecraft
