星载一体化高分辨率微小卫星精密热控制  

Precision Thermal Control of High Resolution Micro-satellite of Platform and Payload Integration

作　　者：柏添 姜峰 孔林 张雷 王建超 BAI Tian;JIANG Feng;KONG Lin;ZHANG Lei;WANG Jianchao(Chang Guang Satellite Technology Co.,Ltd.Changchun 130000,China;School of Mechatronics Engineering,Harbin Institute of Technology,Harbin 150000,China)

机构地区：[1]长光卫星技术股份有限公司,长春130000 [2]哈尔滨工业大学机电工程学院,哈尔滨150000

出　　处：《光子学报》2024年第12期81-92,共12页Acta Photonica Sinica

基　　金：吉林省发展与改革委员会产业技术研究与开发项目(No.2021C45-1)。

摘　　要：星载一体化卫星集成度高,精密控温面临挑战,为了确保卫星成像质量,要实现相机结构温度稳定性全周期≤±0.1℃,焦面传感器温度在成像期间温升≤1℃/min。首先分析卫星布局、飞行轨道热流环境特点及热设计难点,对单机进行均温化设计,针对相机不同组件的温度变化特性,采取辐射加热和相变储能的热设计方法实现高精度温度控制。然后建立数值分析模型并完成了仿真计算。最后开展整星热平衡试验,完成在轨飞行验证。试验与在轨温度结果显示,单机组件温度处于0~35℃,相机组件温度处于19.5~20.5℃,温度波动<±0.05℃,焦面传感器温度为15~20℃,工作时温升速率<0.5℃/min,满足卫星的控温指标与成像需求,验证了热设计方法合理可行。In recent years,there has been an explosive development of micro satellites,and many high-performance micro optical remote sensing satellites have been launched.Integrated design of satellite platform and payload is a method to reduce weight and improve performance.The integrated design of optical payload and platform brings great challenges to heat dissipation and high precision thermal control of optical payload.In order to ensure the imaging quality of the satellite,the temperature stability of the optical payload should be less than±0.1℃throughout the entire life cycle,and the temperature rise of CCDs is less than 1℃/min during imaging.Firstly,the overall layout of the satellite is presented,the orbital heat flux under different conditions has been analyzed.Due to the fact that the-Z plate of the satellite faces the cold space,the-Z plate absorbs the minimum space heat flux and has the strongest heat dissipation capacity.Therefore,the bottom plate in-Z direction is selected as the heat dissipation window for the entire satellite.Electronical components are designed reasonably to achieve temperature equalization.The maximum power of electronic components is 252 W.Reasonably set up heat dissipation channels to ensure that the temperature of electronic components will not be too high,which will affect its reliability and payload temperature stability.To realize the goal of precise temperature control for the optical payload,the calibration for the temperature sensor and measurement are proposed,ultimately enabling the temperature measurement accuracy on board to be controlled within 0.01℃.And the temperature control of the secondary mirror is achieved through the use of radiation heating,which makes the temperature fluctuation of the mirror less than±0.05℃.Pyrolytic graphite sheets are used to improve the thermal conductivity of the optical structures by more than 10 times,creating a more uniform temperature field.The thickness of the pyrolytic graphite sheets is 1.5 mm and its thermal conductivity is

关 键 词：遥感卫星 星载一体化 精密热控 热试验 在轨验证 

分 类 号：V455[一般工业技术—材料科学与工程] V455.8