孙日思, 尹茂贤, 王翠林, 等. 框架镂空结构微小卫星热控设计方法[J]. 航天器环境工程, 2024, 41(3): 336-341 DOI: 10.12126/see.2023150
引用本文: 孙日思, 尹茂贤, 王翠林, 等. 框架镂空结构微小卫星热控设计方法[J]. 航天器环境工程, 2024, 41(3): 336-341 DOI: 10.12126/see.2023150
SUN R S, YIN M X, WANG C L, et al. A thermal control design method for micro-satellites with frame hollow-out structure[J]. Spacecraft Environment Engineering, 2024, 41(3): 336-341. DOI: 10.12126/see.2023150
Citation: SUN R S, YIN M X, WANG C L, et al. A thermal control design method for micro-satellites with frame hollow-out structure[J]. Spacecraft Environment Engineering, 2024, 41(3): 336-341. DOI: 10.12126/see.2023150

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

  • 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。

     

    Abstract: In view that there is no traditional heat dissipation surface for micro-satellites with frame hollow-out 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 low-cost 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.

     

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