| 航天器舷窗区域的热控设计和理论分析 |
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| 引用本文： | 张加迅.航天器舷窗区域的热控设计和理论分析[J].中国空间科学技术,2005,25(4):8-13. |
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| 作者姓名： | 张加迅 |
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| 作者单位： | 中国空间技术研究院,北京,100094 |
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| 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。
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| 关 键 词： | 热管 舷窗 热控制 设计 航天器 热控设计 等效导热系数 材料技术 热管技术 数学模型 |
| 收稿时间： | 2004-06-28 |
| 修稿时间： | 2004-06-282004-11-09 |
The Thermal Control Design and Simplified Theoretical Analysis of the Porthole Area in Spacecraft |
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| Zhang Jiaxun.The Thermal Control Design and Simplified Theoretical Analysis of the Porthole Area in Spacecraft[J].Chinese Space Science and Technology,2005,25(4):8-13. |
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| Authors: | Zhang Jiaxun |
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| Abstract: | 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. |
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| Keywords: | Heat pipe Light port Thermal control Design Spacecraft |
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