Attitude Control of Underactuated and Momentum-Biased Satellite Using State-Dependent Riccati Equation Method
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This paper deals with the attitude control problem of an underactuated satellite controlled by two reaction wheels. The angular momentum of the satellite is assumed to be non-zero or biased. Under these conditions, rotation to arbitrary attitude (roll, pitch, and yaw) is not possible, but direction or limited attitude control (roll and pitch) is possible. For such control, a nonlinear controller is proposed to utilize the angular momentum as gyroscopic torque. The controller is designed using the State-Dependent Riccati Equation (SDRE) method. This SDRE method provides a systematic way to design nonlinear controllers for diverse combinations of two reaction wheels. The proposed method has been verified by numerical simulations and the designed control system works satisfactorily.
KeywordsSatellite attitude control Underactuated Momentum bias Two reaction wheels State-dependent Riccati equation method
This paper was supported by Sunchon National University’s Center for Aerospace Engineering Research in 2018.
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