摘要
为保证航空相机在平流层空间热环境下稳定运行,对无载荷舱的航空相机进行热设计和验证。基于20 km海拔高度下相机外部的对流及辐射环境特点,采用一维对称平板测试法确定选取多层隔热组件作为相机蒙皮材料,选取聚氨酯泡沫作为隔热填充材料。对载荷相机进行热控系统设计,并利用有限元软件分析极端工况下相机的温度场分布,最终设计热控总功率为240 W,包含为相机镜头除霜预留的部分热控功率。低气压热平衡试验验证结果与仿真分析结果吻合良好;低温工况下热控功率约占总功率的70%,控温点的温度波动在±1℃以内,满足相机控温精度要求。
In order to ensure the stable operation of the aerial camera in the thermal environment of the stratospheric space,this paper carries out the thermal design and the verification of an aerial camera without payload module.Based on the characteristics of the convection and radiation environment outside the camera at an altitude of 20 km,the multi-layer thermal insulation component is selected as the camera skin material.The thermal control system of the load camera is designed,and the temperature field distributions under extreme conditions are analyzed using the finite element software.The final total thermal control power is designed as 240 W,with some space to enable the defrosting capability of the camera at the lens.Then,a low-pressure thermal balance test is carried out to verify that the test results are in good agreement with the simulation analysis results.The thermal control power accounts for about 70%of the total power under low temperature conditions,and the temperature fluctuation at the temperature control point is within±1℃,which meets the temperature accuracy requirements.
作者
张源博
孔林
李强
申明
于群
ZHANG Yuanbo;KONG Lin*;LI Qiang;SHEN Ming;YU Qun(Chang Guang Satellite Technology Co.Ltd.,Changchun 130000,China;College of Automotive Engineering,Jilin University,Changchun 130000,China)
出处
《航天器环境工程》
北大核心
2022年第2期153-160,共8页
Spacecraft Environment Engineering
基金
吉林省科技厅项目(编号:20180201106GX)。
关键词
工程热物理
航空相机
热控设计
热试验
engineering thermophysics
aerial camera
thermal control design
thermal test
作者简介
张源博(1995-),男,硕士学位,主要研究方向为航天器热控制技术。E-mail:zhangyuanbo1995@163.com;通信作者:孔林(1986-),男,博士学位,主要研究方向为航天器热控制、空间相机集成分析等。E-mail:konglin@charmingglobe.com。
