框架镂空结构微小卫星热控设计方法  

A thermal control design method for micro-satellites with frame hollow-out structure

作　　者：孙日思 尹茂贤 王翠林 杨子鹏 吴昊天 SUN Risi;YIN Maoxian;WANG Cuilin;YANG Zipeng;WU Haotian(Foshan China Academy of Space Technology Innovation Center,Foshan 528200,China;Shenzhen Aerospace Dongfanghong Satellite,Co.,Ltd.,Shenzhen 518054,China)

机构地区：[1]佛山中国空间技术研究院创新中心,佛山528200 [2]深圳航天东方红卫星有限公司,深圳518054

出　　处：《航天器环境工程》2024年第3期336-341,共6页Spacecraft Environment Engineering

摘　　要：针对框架镂空结构微小卫星无传统散热面的问题,文章提出一种在极低成本和极低重量约束下的小卫星热控设计方法:将低成本的工业级碳纳米铜箔贴装于设备与卫星结构之间,构建柔性导热通道;在镂空结构外侧贴装镀锗聚酰亚胺膜,利用其红外透射率特性使得设备部分热耗辐射至深空冷背景。采用该方法设计的“仰望一号”卫星的在轨遥测数据表明:整星设备温度为13~30℃,满足设计指标要求。所提方法可为此类镂空结构卫星提供热控设计参考。In view that there is no traditional heat dissipation surface for micro-satellites with frame hollowout structure,a thermal control design method for micro-satellites under constraints of extremely low cost and low weight was proposed in this paper.A flexible thermal conductive channel was constructed by attaching lowcost industrial grade carbon nano-copper foil between the equipment and the satellite structure.A germanium coated polyimide film was fastened on the outer side of the hollow-out structure to take advantage of the infrared transmittance of the film to radiate part of the heat of the equipment to the deep space cooling background.The in-orbit telemetry data of Yangwang-1 satellite with application of the proposed method shows that the temperature of the entire satellite equipment is 13℃to 30℃,meeting the design index requirements.The proposed method may provide a reference for the thermal control design of similar hollow-out structured satellites.

关 键 词：微小卫星 热控设计 框架镂空结构 碳纳米铜箔 镀锗聚酰亚胺膜 

分 类 号：V57[航空宇航科学与技术—航空宇航推进理论与工程]