Abstract
Conventional passive thermal design failed to satisfy CCD’s temperature requirement on a geostationary earth orbit satellite Imager camera because of the high power and low working temperature, leading to utilization of thermoelectric cooler (TEC) for heat dissipation. TEC was used in conjunction with the external radiator in the CCDs’ thermal design. In order to maintain the CCDs at low working temperature, experimental research on the performance of thermoelectric cooler was necessary and the results could be the guide for the application of TEC in different conditions. The experimental system to evaluate the performance of TEC was designed and built, consisting of TEC, heat pipe, TEC mounting plate, radiator and heater. A series of TEC performance tests were conducted for domestic and oversea TECs in thermal vacuum environment. The effects of TEC’s mounting, input power and heat load on the temperature difference of TEC’s cold and hot face were explored. Results demonstrated that the temperature difference of TEC’s cold and hot face was slightly increased when TEC’s operating voltage reached 80% of rating voltage, which caused the temperature rise of TEC’s hot face. It recommended TEC to operate at low voltage. Based on experiment results, thermal analysis indicated that the temperature difference of TEC’s cold and hot face could satisfy the temperature requirement and still had surplus.
Published Version
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