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长春光学精密机械与物... [1]
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会议论文 [1]
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2010 [1]
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Analysis of inertia dyadic uncertainty for small agile satellite with control moment gyros (EI CONFERENCE)
会议论文
2010 IEEE International Conference on Mechatronics and Automation, ICMA 2010, August 4, 2010 - August 7, 2010, Xi'an, China
Sun Z.
;
Zhang L.
;
Jin G.
;
Yang X.
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提交时间:2013/03/25
With the increasing demands for the agility of the next earth imaging satellite
control moment gyro (CMG) is considered to be the most suitable actuator because of its torque amplification capability. However
a CMG system may introduce uncertainty of inertia dyadic to a satellite's attitude control system. The uncertainty is negligible for large space vehicles
but it has not been tested whether it can be ignored for small agile satellites. How to model the CMG system inertia dyadic varying with gimbal angles
and what influence it will put on the performance of attitude control system haven't been test accurately as well. All of them are dealt with mathematically and accurately in this paper. This paper firstly gives mathematic descriptions of the inertia dyadic of the 4-CMG pyramid configuration system
varying with gimbal angles
and then designs a variable structure control law for small agile satellite using CMGs. Finally
numerical simulation suggests that the inertia dyadic variation of a 4-CMG pyramid configuration system is approximately centesimal of the total inertia dyadic of the satellite
and that the designed variable structure control law is of good robust performance for an example of large-angle attitude maneuver
despite of the variation of the inertia dyadic. 2010 IEEE.
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