TY - GEN
T1 - Attitude Maneuvering Sequence Design of High-Precision Ground Target Tracking Control for Multispectral Earth Observations
AU - Fujita, Shinya
AU - Sato, Yuji
AU - Kuwahara, Toshinori
AU - Sakamoto, Yuji
AU - Yoshida, Kazuya
N1 - Publisher Copyright:
© 2019 IEEE.
PY - 2019/4/25
Y1 - 2019/4/25
N2 - Microsatellites, weigh less than 100 kg attract attention due to recent growth of space business. Space Robotic Laboratory (SRL) of Tohoku University is currently developing a 50-kg-class Earth observation microsatellite RISESAT, and it is planned to be launched in 2019. RISESAT is equipped with 680 bands and 4 m resolution multispectral Earth observation system which is world's highest performance regardless of satellite size. To carry out the observation, RISESAT has to track a ground target with an accuracy of 0.1°. In this paper, we propose attitude maneuver sequence design which enables high-precision and reliable attitude determination by star trackers. Spiral scan algorithm to enlarge observation area is also derived. Evaluations of the algorithm were carried out by a simulator 'MEVI\mu \mathrm {S}' which is a Hardware-In-the-Loop Simulation (HILS) environment developed by SRL. We confirm that the algorithm satisfies the mission requirements under the influence of sensor noise and computation time limits.
AB - Microsatellites, weigh less than 100 kg attract attention due to recent growth of space business. Space Robotic Laboratory (SRL) of Tohoku University is currently developing a 50-kg-class Earth observation microsatellite RISESAT, and it is planned to be launched in 2019. RISESAT is equipped with 680 bands and 4 m resolution multispectral Earth observation system which is world's highest performance regardless of satellite size. To carry out the observation, RISESAT has to track a ground target with an accuracy of 0.1°. In this paper, we propose attitude maneuver sequence design which enables high-precision and reliable attitude determination by star trackers. Spiral scan algorithm to enlarge observation area is also derived. Evaluations of the algorithm were carried out by a simulator 'MEVI\mu \mathrm {S}' which is a Hardware-In-the-Loop Simulation (HILS) environment developed by SRL. We confirm that the algorithm satisfies the mission requirements under the influence of sensor noise and computation time limits.
UR - http://www.scopus.com/inward/record.url?scp=85065671916&partnerID=8YFLogxK
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U2 - 10.1109/SII.2019.8700434
DO - 10.1109/SII.2019.8700434
M3 - Conference contribution
AN - SCOPUS:85065671916
T3 - Proceedings of the 2019 IEEE/SICE International Symposium on System Integration, SII 2019
SP - 153
EP - 158
BT - Proceedings of the 2019 IEEE/SICE International Symposium on System Integration, SII 2019
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 2019 IEEE/SICE International Symposium on System Integration, SII 2019
Y2 - 14 January 2019 through 16 January 2019
ER -