航天器工程2025，Vol.34Issue(1)：95-100,6.DOI:10.3969/j.issn.1673-8748.2025.01.016
亚太6E卫星电推进分系统设计与验证
Design and Verification of Electric Propulsion Subsystem for APSTAR-6E Satellite
邹达人 1李烽 2刘家涛 3张浩石 1李晨光 1高俊 1王宝军1
作者信息
- 1. 北京控制工程研究所,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
- 3. 兰州空间技术物理研究所,兰州 730000
- 折叠
摘要
Abstract
Electric propulsion has the characteristics of high specific impulse and long lifespan,which can reduce propellant consumption to enhance payload capacity without increasing the satellite launch mass.The design of electric propulsion subsystem including configuration and composition is introduced for APSTAR-6E satellite,the China's first high earth orbit all-electric propulsion satellite.Electrical parameters and temperature characteristics during in-orbit opera-tions are also introduced.The APSTAR-6E satellite has validated ion and Hall electric propulsion technologies for orbital transfer,as well as the compatibility of dual-mode ion and Hall electric propulsion subsystem,and its electric propulsion subsystem design can be applied to other spacecraft.关键词
亚太6E卫星/电推进分系统/离子电推进/霍尔电推进Key words
APSTAR-6E satellite/electric propulsion subsystem/ion electric propulsion/Hall elec-tric propulsion分类
航空航天引用本文复制引用
邹达人,李烽,刘家涛,张浩石,李晨光,高俊,王宝军..亚太6E卫星电推进分系统设计与验证[J].航天器工程,2025,34(1):95-100,6.
