TY - GEN
T1 - Singularity avoidance of control moment gyros using optimization of initial gimbal angles and application to multi target pointing for satellite attitude control
AU - Nanamori, Yasuyuki
AU - Takahashi, Masaki
AU - Taniwaki, Shigemune
AU - Yoshida, Kazuo
AU - Ohkami, Yoshiaki
PY - 2008
Y1 - 2008
N2 - Control Moment Gyros (CMG) has been expected to be applied to an earth observing satellite in recent years. However it is not easy to control it because CMG has a singularity condition and a major source of disturbance. Although there are many singularity avoidance logics, these use much resource of computer mounted on satellite. From the previous background, this paper presents a new but simple CMG steering law using preferred initial gimbal angles and null motion for high accurate attitude control system on an agile satellite. Preferred initial gimbal angles are decided by evaluating function considering inner state of CMG.
AB - Control Moment Gyros (CMG) has been expected to be applied to an earth observing satellite in recent years. However it is not easy to control it because CMG has a singularity condition and a major source of disturbance. Although there are many singularity avoidance logics, these use much resource of computer mounted on satellite. From the previous background, this paper presents a new but simple CMG steering law using preferred initial gimbal angles and null motion for high accurate attitude control system on an agile satellite. Preferred initial gimbal angles are decided by evaluating function considering inner state of CMG.
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M3 - Conference contribution
AN - SCOPUS:60349127595
SN - 9780877035435
T3 - Advances in the Astronautical Sciences
SP - 2337
EP - 2352
BT - Astrodynamics 2007 - Advances in the Astronautical Sciences, Proceedings of the AAS/AIAA Astrodynamics Specialist Conference
ER -