为保证CCD器件处于较小的温度波动范围，针对具有多姿态变化特点的空间相机，进行了CCD焦面组件热控系统的设计。根据具有不同温度膨胀系数的材料遇热变形不同的原理,设计了该热控系统的关键部件－热开关。基于轨道分析计算所得到的地球阴影数据和太阳矢量方向变化的情况，考虑了相机本体的遮挡关系，并结合相机姿态变化的特点，提出了由热开关控制双辐射板散热的方案，对此热控系统进行了具体的热设计。利用TMG软件建立相机的热模型并进行了计算机仿真。结果显示，仅采用被动热控措施的CCD焦面组件温度波动为12.34 ℃，而同时采用主动、被动热控措施后温度波动减小为1.73 ℃，满足热控指标的要求，表明热设计合理、有效。

In order to keep the temperature of CCDs on an attitude varied space camera within a limited range, a thermal control system of the CCD Focal Plane Assembly (CFPA) is designed. Base on the theory of differential thermal expansion between the two materials having different CTE values,a thermal switch as a crucial part in the thermal control system is designed. According to the calculation of the orbit, the obstructive relation of all parts and the characteristics of attitude varying, the scheme of two radiators controlled by a thermal switch is presented, and the thermal design of the CFPA is specified. The performance of the thermal design is simulated by the TMG software. The results indicate that the temperature fluctuation of the CCD is 12.34 ℃ under passive-thermal-control, whereas it is only 1.73 ℃ under both passive-thermal-control and active-thermal-control. Experiments show the thermal control system can meet the need of the mission and the thermal design is efficient and reasonable.