Attitude Control of Momentum-Biased Satellites Equipped with Control Moment Gyroscopes
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This paper deals with the attitude control problem of a satellite using control moment gyroscopes (CMGs). CMGs usually suffer from singularity problems. A method is proposed using non-zero or biased angular momentum of a satellite to avoid the singularity issue. The key concept of the method is using gyroscopic torque due to the angular momentum as the auxiliary torque. For this purpose, a nonlinear controller is designed using the state-dependent Riccati equation method and it is proven that such a nonlinear controller is possible for certain conditions. Furthermore, the proposed method greatly reduces the number of singularity configurations that are not manageable. Simulation examples show that the proposed method works satisfactorily.
KeywordsSatellite attitude control Single-gimbal control moment gyroscope Singularity tolerance Momentum bias State-dependent Riccati equation method
This research was supported by “Space Core Technology Development Program” funded by the Ministry of Science and ICT, Republic of Korea (no. 2017M1A3A3A02016).
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