航天器工程2024，Vol.33Issue(4)：65-70,6.DOI:10.3969/j.issn.1673-8748.2024.04.009
半柱段体装太阳电池片在轨受晒效率分析
In-orbit Sunshine Efficiency of Semi Cylindrical Body-mounted Solar Panels
钱程俊 1常亮 2吴会英 2唐涛2
作者信息
- 1. 中国科学院微小卫星创新研究院,上海 201306||中国科学院大学,北京 100049||上海微小卫星工程中心,上海 201210
- 2. 中国科学院微小卫星创新研究院,上海 201306||上海微小卫星工程中心,上海 201210
- 折叠
摘要
Abstract
For cylindrical spacecraft equipped with semi-cylindrical body-mounted solar panels,the sunshine efficiency of panels'curved surface Σ is maximized when the section ΣA's normal n and the solar vector μso is aligned.In a 2-D sun-pointing mode,the efficiency is highest when the sec-tions normal vector is aligned with the solar vector.In a 1-D sun-pointing mode,sunshine effi-ciency is influenced by the orbital solar angle β.Specifically,the efficiency decreases as the abso-lute value of the orbital solar angle|β|decreases.In a fixed attitude mode,sunshine efficiency improves as the normal vectorn of section ΣA's approaches the Y-axis relative to the solar vector μso.For spacecraft requiring a fixed attitude during in-orbit missions(e.g.,docking,grasping),it is advisable to design the spacecraft structure such that the normal vectorn of the panel section ΣA is oriented closer to the Y-axis relative to the solar vector μso.关键词
体装太阳电池片/受晒效率/柱形航天器/自主任务规划Key words
body-mounted solar panel/sunshine efficiency/cylindrical spacecraft/autonomous mission planning分类
航空航天引用本文复制引用
钱程俊,常亮,吴会英,唐涛..半柱段体装太阳电池片在轨受晒效率分析[J].航天器工程,2024,33(4):65-70,6.
