Feedback control with nominal inputs for agile satellites using control moment gyros

Y. Kusuda, M. Takahashi

研究成果: Article査読

20 被引用数 (Scopus)

抄録

Satellites orbiting the Earth require large-angle and rapid rotational maneuverability. Control moment gyros are expected to be applied to attitude control actuators of small agile satellites, because control moment gyros can generate high torque effectively. However, the control moment gyro has a singularity problem that affects its energy consumption and rapid actuation. To solve the problem, a feedforward control logic using an energy-optimal path planned by a Fourier basis algorithm is proposed here. However, this logic alone cannot maintain precise control under actual errors and disturbances. Therefore, a feedback control system was also designed in order to acquire robustness against errors and disturbances. The designed system included in this paper is characterized by using a system's limit state, which is a newly defined variable, and is predicted by numerical integrals using nominal control inputs. Several numerical simulations and experiments were carried out to verify the feasibility of the proposed logic in terms of the robustness, energy consumption, and the safe use of the control moment gyro.

本文言語English
ページ(範囲)1209-1218
ページ数10
ジャーナルJournal of Guidance, Control, and Dynamics
34
4
DOI
出版ステータスPublished - 2011

ASJC Scopus subject areas

  • 制御およびシステム工学
  • 航空宇宙工学
  • 宇宙惑星科学
  • 電子工学および電気工学
  • 応用数学

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