Page 64 - 《真空与低温》2026年第2期

第 32 卷 第 2 期 真空与低温
2026 年 3 月 Vacuum and Cryogenics 183

空 间 光 学 载 荷 CCD 组 件 辐 射 制 冷 精 密 温 控 设 计 及 验 证

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桂利佳 ，李言青 ，徐文杰 ，李叶飞 ，石恩涛 2
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（1. 上海卫星工程研究所，上海 201109；2. 中国科学院国家空间科学中心，北京 100190）
摘要：针对臭氧总量探测仪中使用的大阵面 CCD 探测器，在无 TEC 制冷模块的情况下，提出了一种基于辐射
制冷的精密控温设计。考虑到探测仪在卫星上的特定布局和结构特性，为 CCD 组件设计了专用的面积 0.36 m 2
的散热板，布局于星体载荷舱+Y 侧桁架上，作为 CCD 芯片的专用散热面。通过采用柔性石墨膜和热管结合的技
术，建立了可靠的传热路径，确保了 CCD 芯片的低温高稳定性运行。为最大限度减少寄生漏热，在散热路径沿途
关键界面处采用了聚酰亚胺隔热垫进行隔热设计，并对各界面当量热阻进行了详细计算和优化。在 CCD 热沉
部分，设计了多路小功率加热器（每路 2.5 W，每通道两主一备），并结合了精密的 PID 控温策略，以实现 mK 量级
的精密温度控制。热仿真结果表明，两个探测通道的 CCD 芯片温度能稳定控制在−33 ℃，且温度稳定性优于
±0.03 ℃，满足了指标要求；在轨遥测结果与热仿真结果一致性良好，证实了热设计的有效性和准确性。该论文的
热设计方法对于类似 CCD 组件的热控设计具有重要的参考和借鉴价值。
关键词：CCD 组件；辐射制冷；精密控温；热仿真；在轨验证
中图分类号：TB69 文献标志码：A 文章编号：1006-7086（2026）02-0183-07
DOI：10.12446/j.issn.1006-7086.2026.02.009

Radiative Cooling-based Precision Thermal Control for Space Optical Payload CCD Assembly:
Design and Verification

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GUI Lijia ，LI Yanqing ，XU Wenjie ，LI Yefei ，SHI Entao 2
（1. Shanghai Institute of Satellite Engineering，Shanghai 201109，China；
2. National Space Science Center，Chinese Academy of Sciences，Beijing 100190，China）
Abstract：A radiation cooling-based precision thermal control subsystem design is proposed to address the critical ther-
mal management challenge for large-format CCD detectors utilized in total ozone sounding instruments， which are not
equipped with thermoelectric cooling (TEC) modules. Given the stringent layout restrictions and unique structural character-
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istics of the satellite-borne instrument，a dedicated heat dissipation plate with an area of 0.36 m is specifically engineered for
the CCD assembly and mounted on the satellite's +Y side truss. Efficient thermal conduction paths are successfully estab-
lished through the synergistic utilization of flexible graphite film and heat pipe technology，thereby guaranteeing the low-tem-
perature operation and long-term thermal stability of the CCD sensors. To minimize parasitic heat leakage，polyimide ther-
mal insulation pads are strategically deployed at critical interfaces along the heat transfer path，with equivalent thermal resis-
tances carefully calculated and optimized. At the CCD cold sink interface，an array of multi-channel low-power heaters （2.5 W
each，two primary and one backup per channel） is strategically deployed and integrated with advanced proportional-integral-
derivative （PID） control algorithms to achieve precise temperature regulation at the millikelvin level. Comprehensive ther-
mal simulation analyses reveal that the CCD chip temperatures across both detection channels can be accurately controlled at
−33 ℃ with exceptional stability exceeding ±0.03 ℃，thereby satisfying all technical requirements. The remarkable consis-
tency observed between in-orbit telemetry data and pre-launch thermal modeling results effectively confirms the reliability
and predictive accuracy of the thermal design methodology. This innovative thermal engineering approach provides substan-
tial reference value and practical guidance for the development of thermal control solutions for analogous CCD-based detec-
tor systems in future space missions.
Key words：CCD component；radiative cooling；precision temperature control；thermal simulation；verification in-orbit

收稿日期：2026−01−16
基金项目：国家重点研发计划项目（2022YFB3903203-2）
作者简介：桂利佳，硕士，高级工程师，E-mail：guilijia_1985@163.com