TY - GEN
T1 - Design and Evaluation of Thruster Control Approach for Micro-satellite ALE-2
AU - Sato, Yuji
AU - Fujita, Shinya
AU - Kuwahara, Toshinori
AU - Shibuya, Yoshihiko
AU - Kamachi, Koh
AU - Kawaguchi, Junichiro
AU - Kubo, Yuki
AU - Nada, Yuichiro
AU - Ohashi, Kaoru
N1 - Funding Information:
The authors are grateful to ALE Co., Ltd. and Patchedconics, LLC for their technical support. This research is supported by JSPS KAKENHI Grant Number JP19J10676 and Tohoku University Division for Interdisciplinary Advanced Research and Education.
Publisher Copyright:
© 2020 IEEE.
PY - 2020/1
Y1 - 2020/1
N2 - This paper provides the thruster control approach for micro-satellites to realize autonomous orbit and attitude control. The Space Robotics Laboratory (SRL) of Tohoku University and ALE Co. Ltd. are currently developing a micro-satellite called 'ALE-2' to generate artificial meteors. This satellite is required to keep the sun-synchronous orbit at the altitude of 375-400 km due to operational safety and mission constraints. ALE-2 is equipped with the High Density Cold Gas Jet System (HDCGJ) developed by Patchedconics, LLC for orbit and attitude control. Although a variety of thruster control methods have been proposed, this research focuses on a design of a reliable, uncomplicated and robust algorithm using the low-thrust, 4 nozzle propulsion system. A precomputed thruster selection table is utilized to reduce the processing power and to optimize the thrust force and torque distribution. The evaluation result from the full-software closed-loop simulation demonstrated that the proposed approach was valid for the orbit control of ALE-2 while high attitude control stability could be maintained in the long term.
AB - This paper provides the thruster control approach for micro-satellites to realize autonomous orbit and attitude control. The Space Robotics Laboratory (SRL) of Tohoku University and ALE Co. Ltd. are currently developing a micro-satellite called 'ALE-2' to generate artificial meteors. This satellite is required to keep the sun-synchronous orbit at the altitude of 375-400 km due to operational safety and mission constraints. ALE-2 is equipped with the High Density Cold Gas Jet System (HDCGJ) developed by Patchedconics, LLC for orbit and attitude control. Although a variety of thruster control methods have been proposed, this research focuses on a design of a reliable, uncomplicated and robust algorithm using the low-thrust, 4 nozzle propulsion system. A precomputed thruster selection table is utilized to reduce the processing power and to optimize the thrust force and torque distribution. The evaluation result from the full-software closed-loop simulation demonstrated that the proposed approach was valid for the orbit control of ALE-2 while high attitude control stability could be maintained in the long term.
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U2 - 10.1109/SII46433.2020.9026234
DO - 10.1109/SII46433.2020.9026234
M3 - Conference contribution
AN - SCOPUS:85082601867
T3 - Proceedings of the 2020 IEEE/SICE International Symposium on System Integration, SII 2020
SP - 477
EP - 482
BT - Proceedings of the 2020 IEEE/SICE International Symposium on System Integration, SII 2020
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 2020 IEEE/SICE International Symposium on System Integration, SII 2020
Y2 - 12 January 2020 through 15 January 2020
ER -