A space-borne differential absorption spectrometer is a high precision aerospace optical remote sensor. It obtains hyperspectral, high spatial resolution spectral information by using CCD (charge coupled device) detectors. Since they are key detectors, the performance of the entire instrument is largely determined by CCDs. The temperature of CCD modules has a greater impact on the instrument measurement accuracy. It leads to severe temperature target. Due to the complex and compact structure, it gets harder to cool and control the CCD modules’ temperature. To meet the detector temperature requirement, a thermal control scheme is presented by comprehensively analyzing the structure and power distribution feature of CCD modules as well as the space heat flux at sun-synchronous orbit. Thermal analysis tool I-DEAS/TMG is utilized to compute temperature distribution and fluctuations in several typical operating conditions. The results show that the temperature of CCD in ultraviolet channel is below 22℃, in visible channel is below 15℃; the fluctuation of temperature in different circle is under 2℃. The design of heat conduction path is verified to be rational and efficient to transfer heat from CCDs. The temperature of CCD heating surface is under control and within the preferred range.