CAJ | 학술논문

某地球静止轨道卫星光学相机由于CCD器件功耗较大，并要求处于较低的工作温度水平，经论证确定采用热电制冷器对CCD的温度进行主动控制。设计了热电制冷器性能地面试验装置，分别在大气和真空环境中选用国内外不同型号的热电制冷器进行对比试验研究。试验得到了安装方式对冷热端温差的影响、输入功耗与冷热端温差的对应关系、负载功率与冷热端温差的对应关系以及大气和真空环境对制冷器的性能影响等数据。试验结果表明，在CCD负载下，制冷器冷热端的温差最大可达到45.8℃，能够满足CCD的低温工作需求。
모지구정지궤도위성광학상궤유우CCD기건공모교대，병요구처우교저적공작온도수평，경론증학정채용열전제랭기대CCD적온도진행주동공제。설계료열전제랭기성능지면시험장치，분별재대기화진공배경중선용국내외불동형호적열전제랭기진행대비시험연구。시험득도료안장방식대랭열단온차적영향、수입공모여랭열단온차적대응관계、부재공솔여랭열단온차적대응관계이급대기화진공배경대제랭기적성능영향등수거。시험결과표명，재CCD부재하，제랭기랭열단적온차최대가체도45.8℃，능구만족CCD적저온공작수구。
Because of high power and low temperature level requirement, thermoelectric coolers were used for heat dissipation of CCDs on a geostationary earth orbit satellite camera. Experimental setup for evaluating thermoelectric coolers′ performance was designed. Domestic and oversea thermoelectric coolers were tested in atmosphere and vacuum respectively. Effects of installation, environment pressure, input power and heat load on the temperature difference of thermoelectric coolers′ hot and cold faces were obtained experimentally. The experimental results showed that, for present CCDs′ heat load on a geostationary orbit satellite, the maximum temperature difference between cold and hot faces was 45.8℃, which satisfied the requirement for running at low temperature level.