In order to keep the temperature of CCD on an attitude-varied space camera within a limited range

a thermal control system of CCD focal plane assembly (CFPA) is designed. A thermal switch

which is the crucial part in the thermal control system

is designed with different kinds of materials. Considering the characteristics of structure of the attitude-varied space camera and its orbit

the scheme of two radiators controlling by thermal switch is presented

and the thermal design of CFPA is stated. Performance of the thermal control system was simulated with the code I-DEAS/TMG. It is shown that the temperature fluctuation of CCD is 12.34℃ on the condition of passive-thermal-control

whereas 1.73℃ on the condition of both passive-thermal-control and active-thermal-control. The thermal control system could meet the requirement of mission

the thermal design is effective and reasonable.