摘要
在低目标红外探测器的优化设计中,CO_2探测仪红外探测器组件内热源功耗大。为了满足信噪比要求使得探测器组件目标温度低、精度要求高,解决以上情况下探测器组件的散热问题,提出了主动热控与被动热控相结合、主动热控精密控制的热设计方案,并采用散热翅片加强散热。利用I-DEAS软件对探测器组件进行热分析计算,得到了探测器组件不同工况不同工作模式下的温度变化值,结果表明红外探测器组件温度范围约为-30%^-26℃。热分析计算结果验证了热设计的合理性,所采用的热控方案能够有效的解决大功耗、低目标温度航天器的散热问题。
Infrared detecting component of COz detector has a high heat source power. In order to satisfy the SNR required, low temperature and high precision are needed for the infrared detector. In order to solve this problem, the thermal control measures of active thermal control combined with passive thermal control and precision control though active thermal control were raised. Also the radiating fin was used to enhance dissipate heat. The thermal analysis was carried out with the I-DEAS software and the temperature of the infrared detectors in different conditions and different working modes were obtained. The results show that the temperature of infrared detectors range in -30℃～-26℃. The results of thermal analysis show that the thermaldesign is feasible and reasonable. The thermal control measure can effectively solve the heat loss problem of spacecraft with large power and low target temperature.
出处
《计算机仿真》
CSCD
北大核心
2016年第3期27-31,共5页
Computer Simulation
基金
国家高技术研究发展计划(863计划)资助项目(2010AA1221091001)
关键词
红外探测器
热设计
热分析
Infrared detectors
Thermal design
Thermal analysis
