亚太6E卫星太阳电池阵优化设计与验证  

Optimization Design and Performance Evaluation of Solar Array Applied for APSTAR-6E Satellite

作　　者：李键 章玄 李大伟[1] 邹世纯[2] 王磊[1] 张子亮 魏强[1] 王敏[1] 潘宇倩[1] LI Jian;ZHANG Xuan;LI Dawei;ZOU Shichun;WANG Lei;ZHANG Ziliang;WEI Qiang;WANG Min;PAN Yuqian(Institute of Telecommunication and Navigation Satellites,China Academy of Space Technology,Beijing 100094,China;Tianjin Institute of Power Sources,Tianjin 300384,China)

机构地区：[1]中国空间技术研究院通信与导航卫星总体部,北京100094 [2]中国电子科技集团公司第十八研究所,天津300384

出　　处：《航天器工程》2025年第1期160-165,共6页Spacecraft Engineering

摘　　要：通过对东方红三号E全电推平台首颗星亚太6E卫星任务需求进行分析,识别出辐照环境和热环境更为恶劣、电推进羽流影响以及电源控制与配电单元(PCDU)的首次应用等任务特点,提出了适应全电推卫星的太阳电池阵优化设计思路,包括高效率、抗辐照、轻量化太阳电池片和加厚盖片设计,分阵布局及匹配设计,以及热环境适应性设计。基于卫星变轨及在轨期间太阳电池阵遥测数据开展了性能评估,符合设计预期,可为后续全电推平台卫星太阳电池阵设计提供参考。By analyzing mission requirements of the APSTAR-6E satellite built based on DFH-3E all-electric propulsion platform,the design characteristics of the solar array are identified,including more severe irradiation and thermal environment,the influence of electric propulsion plumes,and the first application of Power Control and Distribution Unit(PCDU).An optimization design for the solar array of the all-electric propulsion satellite is proposed,including the high efficiency,radiation resistance and lightweight solar cell and thickened cover design,solar array layout and connection design,and thermal environment adaptability design.The evaluation of the telemetry data during the orbit transfer and in orbit phases is conducted.Results show that the performance can meet the design requirements.This case can provide design reference for solar array of future all-electric propulsion satellites.

关 键 词：全电推卫星 亚太6E卫星 太阳电池阵 辐照 

分 类 号：V423.4[航空宇航科学与技术—飞行器设计]