Spaceflight performance of silver coated FEP Teflon as a thermal control surface on the IMP-1 spacecraft
Spaceflight performance of silver coated FEP Teflon as a thermal control surface on the IMP-1 spacecraft
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镀银 FEP 特氟龙作为 IMP-1 航天器热控表面的航天性能
DOI：
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发表时间：
1973
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影响因子：
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通讯作者：
R. H. Hoffman
中科院分区：
文献类型：
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作者：
R. H. Hoffman
第二个表面镜面型涂层，即 FEP 聚四氟乙烯上的气相沉积银，被用作 Imp-I 航天器上一项实验的热控制表面。选择该涂层是为了获得该实验所需的低工作温度。该热控面的初始飞行温度为-70.5℃，与预测值-73℃非常接近，处于非常令人满意的水平。由于航天器内部的温度并未达到所需的低水平，因此探测器必须安装在航天器外部，具有良好的空间视野，最好安装在遮挡阳光的区域。当后一种选择被证明无法实现时，探测器被安装在位于航天器外部的铝板上，平行于自转轴但绕太阳矢量旋转。安装板的厚度约为 6.5 英寸 x 7.5 英寸 x 0.125 英寸。为了使安装板在这样的位置达到所需的温度水平，热设计不仅必须最大限度地减少相对温暖的航天器环境的影响，还要最大限度地减少入射太阳能的影响。
A second surface mirror type coating, vapor deposited silver on FEP Teflon, was used as a thermal control surface for one of the experiments aboard the Imp-I spacecraft. This coating was selected to obtain the low operating temperature required for this experiment. Initial flight temperature of this thermal control surface was -70.5 C, very close to the predicted value of -73 C and at a very satisfactory level. Since temperatures within the spacecraft interior are not at this desired low level, the detectors had to be mounted exterior to the spacecraft with a good view of space, preferably in an area shaded from sunlight. When this latter preference proved unobtainable, the detectors were mounted on an aluminum plate located on the exterior of the spacecraft, parallel to the spin axis but rotating about the solar vector. The mounting plate was approximately 6.5 inches by 7.5 inches by 0.125 inches thick. To achieve the desired temperature level with the mounting plate in such a location, the thermal design had to minimize not only the effects of the relatively warm spacecraft environment but also the effects of the incident solar energy.