空间天文望远镜主动制冷焦面结构设计、分析与热实验

Structure Modeling,Analysis and Thermal Experiment of the Active Cooling Focal Plane of Aspace Astronomy Telescope

对某天文卫星的可见光望远镜载荷CCD焦面工作温度需求进行了分析计算。为满足CCD焦面-65℃的工作温度需求,设计了主动制冷焦面结构。采用有限元方法分析了工作温度下热电制冷器和导热胶产生的热应力,结果表明热电制冷器最大应力为14 Mpa,导热胶最大剪切应力为1.2 Mpa,均处于许用安全应力内。研制的焦面组件模拟件顺利通过了真空热试验,验证了焦面组件的制冷性能与安全性。

The CCD focal plane of the visible telescope on an astronomy satellite is analysed.The actively cooling structure of the focal plane is designed to satisfy-65℃ working temperature.The maximum stress of the TEC and the thermal conductive adhesive under the working temperature is fully calculated by the finite element method,the results show that the maximum stress of the TEC is 14MPa and the maximum shear stress of the thermal conductive structure adhesive is 1.2MPa,which is well below the allowable safety stress.The developed focal plane simulator has passed the thermal vaccum test,and also has validated the cooling ability and the safety of the focal plane assembly.