摘要
结合舷窗的热设计原则,提出舷窗区域的热控设计方案。其中,重点对通过热管技术和高导热材料技术来实现等温化进行了说明,并分析了舷窗法兰框在不同传热方向上的等效导热系数。最后,对航天器舷窗区域在轨飞行的典型传热变化过程建立数学模型,并给出其简化的理论解。
In the design scheme, the isothermal design realized by heat pipe technique and highefficiency heat conductance material technique is explained in details. Addtionally, on the basis of the two techniques, the equivalent heat conductance coefficient of the porthole flange in different heat transfer direction is analyzed. Finally, a mathematical model of the characteristic heat transfer process of the porthole is provided as the spacecraft operates in orbit, and its simplified analytical solution is presented.
出处
《中国空间科学技术》
EI
CSCD
北大核心
2005年第4期8-13,共6页
Chinese Space Science and Technology
