首先介绍了用于保证空间目标正常工作常用的辐射散热器分类, 并阐述了其运行模式及使用条件。总结了现有的空间目标红外特性模型, 并进一步分析, 将空间目标外表面区域分为一般区域和辐射散热区域, 建立不同的能量方程。以FY-1C为例, 根据空间目标的轨道特性、材料特性和结构特性, 使用有限单元法分析得到空间目标外表面的温度场分布, 在散热功率为0 W和100 W的情况下, 散热区域温差最大为51.49 ℃。结合温度场分布和轨道特性, 进一步计算得到空间目标在距离5 km的探测系统入瞳处的辐射照度。当目标处于地球阴影区, 目标散热区域接收到的地球自发辐射和地球反射辐射入射角很大, 可以忽略不计, 此时目标的辐射照度在两种散热功率下相差1~2个数量级。在日照区, 由于目标反射辐射的影响, 不同的散热功率只对长波波段的辐射特性有一定影响。

Radiators used to maintain space target functioning normal were introduced. Operating mode and working condition were presented. Current used space target infrared characteristics models were summarized. With further analysis, the outside surface of space target were divided into common area and radiator, and energy equations were built separately. Taking FY-1C as an example, and taking account of orbit, materials and structure, temperature field of the outer surface of space target was calculated using finite element method. When dissipation power was 0 W and 100 W, the biggest temperature difference of radiator was 51.49 ℃. Analyzing the temperature field with orbit, the illumination in entrance pupil of detection system in a distance of 5 km was calculated. When space target was in the shadow of earth, during which the radiation from earth or solar radiation reflected by earth was negligible because of the big incident angle, the illumination of the space target differed by 1-2 orders of magnitude. When space target was under the sun, different dissipation powers can only affect the illumination of long infrared spectra apparently, because of the reflected radiation of target.