Static closed loop test system for attitude control system of micro satellite RISING-2

Kazufumi Fukuda; Yuji Sakamoto; Toshinori Kuwahara; Kazuya Yoshida; Yukihiro Takahashi

doi:10.1109/SII.2011.6147567

Static closed loop test system for attitude control system of micro satellite RISING-2

Kazufumi Fukuda, Yuji Sakamoto, Toshinori Kuwahara, Kazuya Yoshida, Yukihiro Takahashi

ENG - Aerospace Engineering

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

2 Citations (Scopus)

Abstract

50-kg class micro satellite RISING-2 is now under development by Tohoku University and Hokkaido University. The development is at Flight Model phase. The main mission of the RISING-2 is Earth surface observations with 5-m resolution using a Cassegrain telescope with 10-cm diameter and 1-m focal length. Accurate attitude control capability with less than 0.1 deg direction errors and less than 0.02 deg/s angular velocity errors is required to realize this observation. The attitude control system realizes 3-axis stabilization for the observation by means of star sensors, gyro sensors, sun attitude sensors and reaction wheels. In this paper the static closed loop test system for the attitude control system of the RISING-2 is described. This test system is the simulation including the hardware of the attitude control system of the RISING-2. The results of the tests show that the pointing error is very larger than the results of software simulation.

Original language	English
Title of host publication	2011 IEEE/SICE International Symposium on System Integration, SII 2011
Pages	890-895
Number of pages	6
DOIs	https://doi.org/10.1109/SII.2011.6147567
Publication status	Published - 2011 Dec 1
Event	2011 IEEE/SICE International Symposium on System Integration, SII 2011 - Kyoto, Japan Duration: 2011 Dec 20 → 2011 Dec 22

Publication series

Name	2011 IEEE/SICE International Symposium on System Integration, SII 2011

Other

Other	2011 IEEE/SICE International Symposium on System Integration, SII 2011
Country	Japan
City	Kyoto
Period	11/12/20 → 11/12/22

ASJC Scopus subject areas

Computer Networks and Communications
Control and Systems Engineering

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Fukuda, K., Sakamoto, Y., Kuwahara, T., Yoshida, K., & Takahashi, Y. (2011). Static closed loop test system for attitude control system of micro satellite RISING-2. In 2011 IEEE/SICE International Symposium on System Integration, SII 2011 (pp. 890-895). [6147567] (2011 IEEE/SICE International Symposium on System Integration, SII 2011). https://doi.org/10.1109/SII.2011.6147567

Static closed loop test system for attitude control system of micro satellite RISING-2. / Fukuda, Kazufumi; Sakamoto, Yuji ; Kuwahara, Toshinori ; Yoshida, Kazuya; Takahashi, Yukihiro.

2011 IEEE/SICE International Symposium on System Integration, SII 2011. 2011. p. 890-895 6147567 (2011 IEEE/SICE International Symposium on System Integration, SII 2011).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

Fukuda, K, Sakamoto, Y , Kuwahara, T , Yoshida, K & Takahashi, Y 2011, Static closed loop test system for attitude control system of micro satellite RISING-2. in 2011 IEEE/SICE International Symposium on System Integration, SII 2011., 6147567, 2011 IEEE/SICE International Symposium on System Integration, SII 2011, pp. 890-895, 2011 IEEE/SICE International Symposium on System Integration, SII 2011, Kyoto, Japan, 11/12/20. https://doi.org/10.1109/SII.2011.6147567

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abstract = "50-kg class micro satellite RISING-2 is now under development by Tohoku University and Hokkaido University. The development is at Flight Model phase. The main mission of the RISING-2 is Earth surface observations with 5-m resolution using a Cassegrain telescope with 10-cm diameter and 1-m focal length. Accurate attitude control capability with less than 0.1 deg direction errors and less than 0.02 deg/s angular velocity errors is required to realize this observation. The attitude control system realizes 3-axis stabilization for the observation by means of star sensors, gyro sensors, sun attitude sensors and reaction wheels. In this paper the static closed loop test system for the attitude control system of the RISING-2 is described. This test system is the simulation including the hardware of the attitude control system of the RISING-2. The results of the tests show that the pointing error is very larger than the results of software simulation.",

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