半柱段体装太阳电池片在轨受晒效率分析OA北大核心CSTPCD

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.