航天器环境工程2026，Vol.43Issue(4)：267-272,6.DOI:10.12126/see.2026038
卫星瞬时大功率载荷多级散热方案及验证
Design and verification of a multistage heat dissipation scheme for transient high-power satellite payloads
摘要
Abstract
To address the transient high-power operating characteristics of an AI computing payload onboard a satellite,a multistage heat dissipation scheme integrating phase-change thermal energy storage,grooved heat-pipe heat transfer,and radiative heat dissipation through thermal-control coatings was proposed.The effectiveness of the proposed scheme was verified through thermal simulations and vacuum thermal balance tests.On-orbit data showed that the payload reached a maximum temperature of 36℃during 30 min of continuous operation at a full power of 152.3 W,providing a 14℃margin below the upper temperature limit and satisfying the on-orbit operating temperature requirement.During non-mission periods,the thermal-control power consumption of the satellite platform was 17.6 W per orbit,meeting the design requirement of no more than 30 W.The proposed scheme demonstrates high heat-dissipation capability,a high level of structural integration,low thermal-control resource requirements,and high reliability.It offers a lightweight,low-resource,modular thermal control solution for satellite payloads with transient thermal loads of 100-200 W.关键词
卫星热控制/瞬时大功率载荷/算力载荷/相变储热/多级散热Key words
satellite thermal control/transient high-power payload/AI computing payload/phase-change thermal energy storage/multistage heat dissipation分类
航空航天引用本文复制引用
禹韬,郭涛,冯明鹏..卫星瞬时大功率载荷多级散热方案及验证[J].航天器环境工程,2026,43(4):267-272,6.基金项目
四川省重大科技专项项目(编号:2024ZDZX0013) （编号:2024ZDZX0013）
