| Summary: | 碩士 === 國立交通大學 === 電機與控制工程系 === 89 === The thesis described the study of the practical spacecraft attitude guidance maneuvers to design useful rapid spacecraft attitude controller. We will derive the dynamic equation of the satellite and build its control law according to the different direction angles in this thesis. A PD control law will be used as a small-angle error controller which use optimized maneuvers. The guidance be used on ROCSAT-2. A sliding-mode control (SMC) design technique is proposed for tracking the desired trajectories that are based on spacecraft eigenaxis rotation with maximum torques. The major advantage of eigenaxis rotation with maximum torques is that it provides the minimum-time maneuver. Meanwhile, the SMC controller provides the robust control for removing the effects of model uncertainty. Practical control constraint on wheel torque is also taken into account in the determination of the maximum torques. To improve the undesirable transient response before reaching the sliding manifold, the smooth model sliding-mode control is developed. Two previous developed control schemes, quaternion feedback regulator for spacecraft eigenaxis rotation and near-minimum-time eigenaxis rotation maneuvers with rate-tracking feedback, were adapted to show the superiority of the proposed design method.
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