主动温度控制措施是星载仪器适应空间严酷热环境的重要手段。某星载仪器采用主动加热的的方式对温度敏感组件 进行温度控制。该温控模块的可靠性直接关系到主动温控措施的效果,进而影响仪器任务的成败。以该温控电路 为基础,通过对系统备份和单元备份两种冗余设计方案的可靠性进行了分析对比,结果表明采用系统备份方式 的温控电路可靠度更高,根据该可靠性预计结果,结合该星载温度控制功能模块特点,确定了温控模块的最终实施方案。

Active temperature control is adapted as an important mean for the spaceborne instruments to fit the harsh thermal environment. The way of active heating is used for the spaceborne instrument to control the temperature of its temperature sensitive component. The reliability of the temperature control module is directly related to the effects of the active temperature control measures, which may affect the instrument performance. Based on the temperature control circuit, the reliability comparison between two redundant design schemes is carried out, namely the system backup and the unit backup. The results showed that the backup system has higher reliability. According to the results of the reliability prediction, in combination with the on-board temperature control function module’s feature, the temperature control module was selected.