Agile attitude maneuver via SDRE controller using SGCMG integrated satellite model

Ryotaro Ozawa, Masaki Takahashi

研究成果: Conference contribution

2 被引用数 (Scopus)

抄録

In this research, we propose a design method for a nonlinear optimal attitude control system that combines the systems of a single-gimbal control moment gyro (SGCMG) and a satellite that were conventionally designed separately. For this purpose, we designed a state-dependent linear representation model integrating satellite dynamics and SGCMG dynamics using a State-Dependent Riccati Equation (SDRE) controller. In the proposed method, it is possible to design the gimbal angular velocity as input without solving the inverse kinematics in the pyramid-type SGCMG. Therefore, it is possible to avoid the singularity of SGCMG by designing the weighting function matrices considering the relationship between the maneuvering axis and SGCMG steering. A numerical simulation shows that it is possible to achieve a high-speed attitude maneuver of the satellite by optimal attitude control considering singularity avoidance by the proposed method. In addition, usefulness of proposed law is shown in comparison with the GSR Inverse steering logic for the agile attitude maneuver.

本文言語English
ホスト出版物のタイトルAIAA Guidance, Navigation, and Control
出版社American Institute of Aeronautics and Astronautics Inc, AIAA
210039
ISBN(印刷版)9781624105265
DOI
出版ステータスPublished - 2018 1 1
イベントAIAA Guidance, Navigation, and Control Conference, 2018 - Kissimmee, United States
継続期間: 2018 1 82018 1 12

出版物シリーズ

名前AIAA Guidance, Navigation, and Control Conference, 2018
番号210039

Other

OtherAIAA Guidance, Navigation, and Control Conference, 2018
CountryUnited States
CityKissimmee
Period18/1/818/1/12

ASJC Scopus subject areas

  • Aerospace Engineering
  • Control and Systems Engineering
  • Electrical and Electronic Engineering

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