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装在卫星上的某些遥感器的关键性部件,必须冷却到低温温度,才能获得良好的工作特性。对于长期运行的飞行器,冷却方法的选择余地往往很小,不是采用被动辐射致冷器,就是采用闭式循环致冷机。本文概述了这两种方法的一般能力,并就被动辐射致冷器和致冷机系统(包括太阳电池阵和排热辐射器)的重量和露出面积作了比较。对于不同的致冷器,两种系统的温度和重量(或面积)的关系曲线存在着交叉点,当温度需低于65K 时,致冷机系统具有重量轻和露出面积小的优点。对适用于辐射致冷器的轨道而言,根据可得到的资料分析表明,致冷机系统重量随其交叉点的变化是这样的:致冷量为0.1瓦时,交叉点在67K,10瓦时为94K。这说明随着所需要的冷却能力的增加,致冷机系统越发有吸引力,这是因为较大的致冷机,致冷效率也较高。为改善未来空间应用的致冷机效率,还得采取有效的措施,以减少能源和排热系统的尺寸和重量。
Some of the key components of remote sensors mounted on satellites must be cooled to a cryogenic temperature to achieve good operating characteristics. For long-term operation of the aircraft, the choice of cooling methods tend to be very small, either with passive radiation cooler, is to use closed-cycle cooler. This article outlines the general capabilities of both approaches and compares the weight and exposed area of passive radiators and chiller systems, including solar arrays and radiant emitters. For different chillers, there is a crossover point between temperature and weight (or area) for both systems. The chiller system has the advantages of light weight and small exposed area at temperatures below 65K. Analysis of available data for a rail suitable for a radiofrequency refrigerator shows the change in the weight of the chiller system as it crosses its point of intersection with a 0.1 Kilowatt chiller at an intersection of 67 K at 10 W When 94K. This shows that as the required cooling capacity increases, the chiller system becomes more attractive because larger chillers have higher cooling efficiencies. In order to improve the efficiency of the refrigerator for future space applications, effective measures have also been taken to reduce the size and weight of energy and heat removal systems.