Attitude Maneuver and Gimbal angle guidance by SDRE controller using SGCMG integrated satellite SDLR model

Ryotaro Ozawa, Masaki Takahashi

研究成果: Conference contribution

抜粋

In the conventional agile attitude maneuver of a satellite, a control system of the satellite and Single Gimbal Control Moment Gyro (SGCMG) is designed separately and stability is not guaranteed under the singularity of SGCMGs. Therefore, in this research, we integrate the satellite and SGCMGs and design a model with the gimbal angular velocity as input. Since the target gimbal angle can be explicitly designed by a null motion, proposed control system is possible to guide the initial gimbal angle which is advantageous for next mission. In addition, it is shown that proposed method can guarantee stability even under the singularity of SGCMGs by the State-Dependent Riccati Equation (SDRE). Moreover, numerical simulations show that the singularity avoidance performance up to the target gimbal angle and the guidance performance of the gimbal angle are higher than the conventional method due to the optimality of gimbal angular velocity input.

元の言語English
ホスト出版物のタイトル2017 Asian Control Conference, ASCC 2017
出版者Institute of Electrical and Electronics Engineers Inc.
ページ1847-1852
ページ数6
2018-January
ISBN(電子版)9781509015733
DOI
出版物ステータスPublished - 2018 2 7
イベント2017 11th Asian Control Conference, ASCC 2017 - Gold Coast, Australia
継続期間: 2017 12 172017 12 20

Other

Other2017 11th Asian Control Conference, ASCC 2017
Australia
Gold Coast
期間17/12/1717/12/20

    フィンガープリント

ASJC Scopus subject areas

  • Control and Optimization

これを引用

Ozawa, R., & Takahashi, M. (2018). Attitude Maneuver and Gimbal angle guidance by SDRE controller using SGCMG integrated satellite SDLR model. : 2017 Asian Control Conference, ASCC 2017 (巻 2018-January, pp. 1847-1852). Institute of Electrical and Electronics Engineers Inc.. https://doi.org/10.1109/ASCC.2017.8287455