Abstract
Studies on attitude controllers for spacecraft by two reaction wheels were started recently. In the research, the optimal trajectories of large angle maneuvers are figured. The required maneuver is a rest-to-rest reorientation around uncontrolled z-axis which is no reaction wheel in this paper. The criterion of the minimum energy problem is given as an integration of the sum of squared torque. The z-axis slants largely during such maneuver. A large z-axis slant causes some attitudinal problems, which are cutting sunlight or breaking the communication links during maneuver and so on. Therefore, this paper treats with the minimum energy problem with slant constraint of z-axis for satellite maneuvers. Numerical solutions are shown and the features of the optimal trajectories are discussed from the equations of motion analytically. The results of this paper could be an effective for minimum energy controllers with attitude constraint
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