亚太6E卫星平台与载荷一体化热控设计与验证  

Integrated Thermal Control Design and Verification of Platform and Payload Devices for APSTAR-6E Satellite

作　　者：乔心全[1] 吕鲁仓 安秀枝 侯卫国[2] 王敏[2] QIAO Xinquan;LYU Lucang;AN Xiuzhi;HOU Weiguo;WANG Min(National Key Laboratory of Spacecraft Thermal Control,Beijing Institute of Spacecraft System Engineering,Beijing 100094,China;Institute of Telecommunication and Navigation Satellites,China Academy of Space Technology,Beijing 100094,China)

机构地区：[1]北京空间飞行器总体设计部航天器热控全国重点实验室,北京100094 [2]中国空间技术研究院通信与导航卫星总体部,北京100094

出　　处：《航天器工程》2025年第1期105-111,共7页Spacecraft Engineering

摘　　要：针对设备或单机的差异化热控需求,航天器热控多数采取分舱设计或分区控温的方案,以实现各舱段或各区域的独立散热和控温,便于对各独立区域内设备或单机进行精准控温;但是分舱设计所需热控资源较多,各独立区域内均需独立配置主动控温功率、控温和测温通道以及热控指令等。以我国首颗全电推通信卫星为典型示例,针对平台与载荷设备的控温需求,通过分析对比分舱(或分区)控温与一体化布局热控设计所需散热面和保温加热功率的差异,从理论分析和在轨验证两方面,详细给出了一体化热控设计带来的有益效果,证明热控方案对“全电推高轨卫星大功率变轨、小功率位保”分时差异化需求的特定适用性。仅以亚太6E卫星为例,整星主散热面9.9m^(2)、载荷热耗1500W,一体化热控设计能够减少散热面需求0.5~1.0m^(2),保温加热功率能够节省600~800W。In response to the different thermal control requirements of equipment and device,spacecraft thermal control design mostly adopts the scheme of multi-cabin thermal design or zone thermal control to achieve independent heat dissipation and precise temperature control.As a result of independent thermal control,the scheme of multi-cabin thermal design needs more resources of heating power,thermistors,telemetry commands etc.Taking the China’s first fully electric propulsion GEO satellite as a typical example,in view of thermal control requirements of the platform and payload device,the differences between multi-cabin thermal control and integrated thermal design in required heat dissipation surface area and heating power are analyzed and compared in this paper,and the beneficial effects of the integrated thermal design are given in detail,from both theoretical analysis and on-orbit verification.The specific applicability of integrated thermal design scheme to the time-sharing different requirements of“all-electric propulsion high earth orbit satellite with high power orbit transfer and low power position holding”is proved.Taking the APSTAR-6E satellite as an example,its main heat dissipation surface area is 9.9m^(2),the heat load consumption is about 1500W,the integrated thermal design can reduce the heat dissipation area demand by 0.5~1.0m^(2),and the heating power savings can be about 600~800W.

关 键 词：平台与载荷 统一布局 热控设计 全电推 验证 

分 类 号：V423.41[航空宇航科学与技术—飞行器设计]