摘要
针对“巴遥一号”卫星相机主体全寿命周期内温度应保持较高稳定性和均匀性的任务要求。通过建立热阻网络模型,分析热控设计的重点和难点,并提出有效管理热量传递和合理设计控温方式的方法;利用结构热控一体化设计解决双相机焦面电路高功率密度热量排散问题,采用直接与间接相结合的控温方式提高主光学结构温度稳定性。通过热仿真分析和热平衡试验验证热设计的准确性。相机入轨4年后1个月内的在轨温度变化显示,相机各部分温度水平和温度稳定性满足设计指标要求,镜头的温度波动范围在0.09~0.17℃,CCD的温度波动范围在0.93~4.30℃,表明相机热控设计合理有效。以上设计实践可为双相机一体化热控设计提供借鉴。
In response to the mission requirements of maintaining high stability and uniformity of temperature throughout the camera’s lifespan of PRSS-1 satellite,the key points and challenges of thermal control design were analyzed by establishing a thermal resistance network model.In addition,methods for effectively managing heat transfer and designing of thermal control were proposed.An integrated structural thermal control design was employed to solve the difficulty of high-power density heat dissipation in the dual camera focal plane circuit.The temperature stability of the main optical structure was improved by a combination of direct and indirect thermal control methods.The accuracy of thermal design was verified by thermal simulation analysis and thermal balance test.The temperature changes within one month after four years of operation in orbit show that the temperature level and stability of each part of the camera meet the requirements of the design index,with the temperature fluctuation ranging from 0.09℃to 0.17℃for the lens,and from 0.93℃to 4.30℃for the CCD,indicating that the thermal control design is reasonable and effective.The above design practice may provide a reference for the integrated thermal control design of the satellite's dual camera system.
作者
王云彬
阳明
孟庆亮
颜吟雪
于峰
孔庆乐
李立广
韦广朗
张悦
王阳
申洁
WANG Yunbin;YANG Ming;MENG Qingliang;YAN Yinxue;YU Feng;KONG Qingle;LI Liguang;WEI Guanglang;ZHANG Yue;WANG Yang;SHEN Jie(Beijing Institute of Space Mechanics&Electricity,Beijing 100094,China)
出处
《航天器环境工程》
CSCD
2024年第2期151-159,共9页
Spacecraft Environment Engineering
基金
国家自然科学基金项目(编号:51806010)。
关键词
光学遥感相机
热设计
热平衡试验
在轨验证
optical remote sensing camera
thermal design
thermal balance test
in-orbit verification