Attitude optimization of a spinning solar sail via spin-rate control to accelerate in tangential direction

Go Ono, Yuya Mimasu, Jun'ichiro Kawaguchi

研究成果: Conference article査読

2 被引用数 (Scopus)

抄録

The spin axis direction of a spinning solar sail rotates around an equilibrium point near the Sun direction due to the influence of solar radiation pressure. This characteristic may lead to a complexity in the attitude control of the spacecraft. The objective of this research is to derive an optimal spin-rate control law for a spinning solar sail to maximize the solar radiation pressure acceleration in the tangential direction of its orbit. An analytical solution of a bang-bang control of the spin rate is derived using the calculus of variations, and its validity is verified with a numerical analysis. The control law determined in this study enables a spinning solar sail to accelerate continuously and explore the solar system.

本文言語English
ページ(範囲)2583-2596
ページ数14
ジャーナルAdvances in the Astronautical Sciences
148
出版ステータスPublished - 2013
外部発表はい
イベント23rd AAS/AIAA Space Flight Mechanics Meeting, Spaceflight Mechanics 2013 - Kauai, HI, United States
継続期間: 2013 2 102013 2 14

ASJC Scopus subject areas

  • 航空宇宙工学
  • 宇宙惑星科学

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