TY - GEN
T1 - Design, Implementation and In-orbit Demonstration of Attitude and Orbit Control System for Micro-satellite ALE-2
AU - Sato, Yuji
AU - Fujita, Shinya
AU - Kuwahara, Toshinori
AU - Shibuya, Yoshihiko
AU - Kamachi, Koh
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:
© 2021 IEEE.
PY - 2021/1/11
Y1 - 2021/1/11
N2 - This paper describes procedures for the design, implementation and in-orbit verification of an advanced Attitude and Orbit Control System (AOCS) that can be applied to micro-satellites. Functional requirements imposed on AOCS are becoming severer as the mission becomes more complicated and challenging even though onboard resources are limited in micro-satellites. In addition, many verification steps must be taken for the system design, implementation, and in-orbit demonstration. In this study, an advanced AOCS design that is optimized for the mission of the artificial meteor demonstration satellite 'ALE-2' is proposed. This paper presents three AOCS features that are specialized to ALE-2 but applicable to other micro-satellites: sensor calibration technique, attitude and gyroscope bias estimation using extended Kalman filter, and orbit control by small propulsion system. These functions were implemented using a hardware-in-the-loop simulator environment, allowing for quick and efficient ground evaluation. In addition, in-orbit demonstration of the proposed AOCS was performed after the launch of ALE-2. Through these verification process, it was confirmed that the AOCS functions required for the mission of ALE-2 were properly implemented and worked in orbit.
AB - This paper describes procedures for the design, implementation and in-orbit verification of an advanced Attitude and Orbit Control System (AOCS) that can be applied to micro-satellites. Functional requirements imposed on AOCS are becoming severer as the mission becomes more complicated and challenging even though onboard resources are limited in micro-satellites. In addition, many verification steps must be taken for the system design, implementation, and in-orbit demonstration. In this study, an advanced AOCS design that is optimized for the mission of the artificial meteor demonstration satellite 'ALE-2' is proposed. This paper presents three AOCS features that are specialized to ALE-2 but applicable to other micro-satellites: sensor calibration technique, attitude and gyroscope bias estimation using extended Kalman filter, and orbit control by small propulsion system. These functions were implemented using a hardware-in-the-loop simulator environment, allowing for quick and efficient ground evaluation. In addition, in-orbit demonstration of the proposed AOCS was performed after the launch of ALE-2. Through these verification process, it was confirmed that the AOCS functions required for the mission of ALE-2 were properly implemented and worked in orbit.
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U2 - 10.1109/IEEECONF49454.2021.9382731
DO - 10.1109/IEEECONF49454.2021.9382731
M3 - Conference contribution
AN - SCOPUS:85103738217
T3 - 2021 IEEE/SICE International Symposium on System Integration, SII 2021
SP - 662
EP - 668
BT - 2021 IEEE/SICE International Symposium on System Integration, SII 2021
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 2021 IEEE/SICE International Symposium on System Integration, SII 2021
Y2 - 11 January 2021 through 14 January 2021
ER -