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.
|ジャーナル||Advances in the Astronautical Sciences|
|出版ステータス||Published - 2013|
|イベント||23rd AAS/AIAA Space Flight Mechanics Meeting, Spaceflight Mechanics 2013 - Kauai, HI, United States|
継続期間: 2013 2 10 → 2013 2 14
ASJC Scopus subject areas