"Recent years have seen a growing requirement for accurate and agile attitude control of spacecraft. In order to both quickly and accurately control the attitude of a spacecraft, Control Moment Gyros (CMGs) which can generate much higher torque than conventional spacecraft actuators are used as an actuator of spacecraft. Rapid maneuverability is needed for spacecraft with CMGs and it needs drive on motors. It is also said that drive on motors negatively affects lifetime of motors. Moreover, it is also important for attitude control systems to be fault tolerant. In this study, a design method is proposed for the attitude control system, using multi objective optimization of the hardware and software parameters. Pareto solutions are obtained using multi objective optimization of Skew angle and the parameters of the control system. The tendency of the evaluation value with or without optimizing Skew angle and with or without consideration of fault-tolerance is discussed."
多目的最適化によるコントロールモーメントジャイロ搭載宇宙機の耐故障性姿勢制御系設計
AC1500049000.pdf
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