Abstract
This study aims at achieving a three axis stabilization attitude control of a satellite using two control moment gyros (CMGs). If this can be achieved, it leads to realization of attitude control system (ACS) with fault tolerance because the loss of the function of ACS is not fatal even if some CMGs mounted on the satellite are broken. In this paper, an underactuated satellite with two CMGs is a controlled system, and both conservation law of angular momentum of satellite and satellite attitude dynamics were formulated. Using the Rodriguez parameter as an attitude representation, satellite attitude kinematics was formulated. In this study, a sliding mode controller using the Rodriguez parameter was designed. To verify the control performance of the designed controller, some numerical simulations were carried out. From some results, we confirmed the effectiveness of the designed controller for controlling the satellite with two CMGs.
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