对空间相机大功率CCD器件进行了热设计以解决其散热问题，为了验证热设计的合理性进行了CCD焦面组件的热试验。首先，介绍了以传导为主要散热措施的CCD器件热设计方案，CCD器件的热量主要通过热管传递到冷源；然后，针对整个焦面组件进行了试验规划，特别对模拟冷板进行了专门设计；最后，在真空环境下进行了综合试验。试验结果显示，功耗为10 W的CCD器件连续工作70 min，在12 ℃冷源的情况下，能够控制焦平面器件的温度<35 ℃。该试验验证了CCD焦面组件热设计的合理性，并为焦面组件热分析计算模型修正提供了依据。

A thermal control system for a high-power CCD space camera was designed, including a thermal test of the focal plane assembly for resolving the heat dissipation problem. First, the thermal design scheme of the CCD was examined,where the heat produced by the CCD was transferred to the cold source through a heat pipe. Then a thermal test of focal plane assembly was planned with the simulated cold source specially designed. Finally, the thermal test of focal plane assembly was performed in a vacuum to simulate its space environment and structure characteristics. The results show that the working temperature of a 10 W high-power CCD space camera can be kept below 35 ℃ when it has been working for 70 min continuously and has a 12 ℃ cool source.The thermal design of the CCD focal plane assembly for the space camera is feasible and acceptable.It can be used as a reference for the mode correction of focal plane assembly thermal analysis.