TY - GEN
T1 - Development of Spin Stabilization Control System for the Cosmic Dust Observation CubeSat
AU - Fujita, Shinya
AU - Ishimaru, Ryo
AU - Sakamoto, Yuji
AU - Maeda, Keisuke
AU - Okudaira, Osamu
AU - Sato, Yuji
AU - Kuwahara, Toshinori
AU - Matsui, Takafumi
N1 - Funding Information:
This work was supported by JSPS KAKENHI Grant Number JP21K14342. The ASTERISC project is supported by Innovative Satellite Technology Demonstration Program of JAXA.
Publisher Copyright:
© 2022 IEEE.
PY - 2022
Y1 - 2022
N2 - The 3U CubeSat "ASTERISC"is a cosmic dust observation satellite developed by Chiba Institute of Technology and Tohoku University, and is planned to be launched in October 2021. ASTERISC is equipped with a new type of large-area dust sensor that uses piezoelectric elements to detect elastic waves induced by micron-sized cosmic dust or small space debris colliding with the polyimide film. Since the dust sensor measures only the magnitude of the momentum of the colliding particles, a system to measure and control the direction of the sensor membrane is required to identify the direction of particle flight. By using the classical spin stabilization method, which is rarely used in CubeSats, this satellite aims to maintain the sensor membrane direction toward the Sun constantly with low power consumption. In this paper, we propose the use of spin stabilization control law with magnetic torquers, a method for deriving the target direction vector, and the design of a cosine coarse sun sensor that is aimed to achieve a field of view about twice as large as the conventional method.
AB - The 3U CubeSat "ASTERISC"is a cosmic dust observation satellite developed by Chiba Institute of Technology and Tohoku University, and is planned to be launched in October 2021. ASTERISC is equipped with a new type of large-area dust sensor that uses piezoelectric elements to detect elastic waves induced by micron-sized cosmic dust or small space debris colliding with the polyimide film. Since the dust sensor measures only the magnitude of the momentum of the colliding particles, a system to measure and control the direction of the sensor membrane is required to identify the direction of particle flight. By using the classical spin stabilization method, which is rarely used in CubeSats, this satellite aims to maintain the sensor membrane direction toward the Sun constantly with low power consumption. In this paper, we propose the use of spin stabilization control law with magnetic torquers, a method for deriving the target direction vector, and the design of a cosine coarse sun sensor that is aimed to achieve a field of view about twice as large as the conventional method.
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U2 - 10.1109/SII52469.2022.9708909
DO - 10.1109/SII52469.2022.9708909
M3 - Conference contribution
AN - SCOPUS:85126247333
T3 - 2022 IEEE/SICE International Symposium on System Integration, SII 2022
SP - 114
EP - 119
BT - 2022 IEEE/SICE International Symposium on System Integration, SII 2022
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 2022 IEEE/SICE International Symposium on System Integration, SII 2022
Y2 - 9 January 2022 through 12 January 2022
ER -