Gimbal angle feedback steering logic for spacecraft with control momentum gyros considering required attitude accuracy

Satoshi Obuse, Masaki Takahashi

研究成果: Paper査読

抄録

This study proposes a steering law of Control Moment Gyros (CMG), which is used for attitude control of spacecraft. Recently, missions of spacecraft such as Earth-observing satellites have required increasingly rapid maneuvering and the CMG has been expected to be applied to the attitude control of spacecraft because it generates high torques. The CMG can generate torque by tracking the gimbal angular velocity to a reference angular velocity derived from a reference torque. However, the CMG has a singularity problem. At singularities, the CMG cannot generate the required torque in the case of a specific set of gimbal angles. Steering logic calculates the gimbal angular velocity for escaping singularities from an indicator of the singularity, and the associated additional torque may adversely affect the attitude control performance of the spacecraft. Near the singularity, the gimbal angular velocity for attitude control torque increases and the singularity escape performance is thus likely to be low. This study proposes a gimbal angle feedback steering logic that improves the singularity escape performance by controlling the gimbal angular velocity for attitude control torque. A design method employing feedback gain related to the singularity escape performance in consideration of the required attitude accuracy is proposed.

本文言語English
出版ステータスPublished - 2014 1月 1
イベント12th International Conference on Motion and Vibration Control, MOVIC 2014 - Sapporo, Hokkaido, Japan
継続期間: 2014 8月 32014 8月 7

Other

Other12th International Conference on Motion and Vibration Control, MOVIC 2014
国/地域Japan
CitySapporo, Hokkaido
Period14/8/314/8/7

ASJC Scopus subject areas

  • 制御およびシステム工学

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