Large angle maneuver and high accuracy attitude pointing steering law for variable speed control momentum gyroscopes |
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| Authors: | Feng Liu Yang Gao Weiwei Zhang |
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| Institution: | 1. School of Mathematics and Statistics, Northeast Normal University, Changchun 130024, China;2. School of Mathematics and Physics, Guangxi University for Nationalities, Nanning 530006, China;1. School of Software Engineering, Anyang Normal University, Anyang 455000, PR China;2. Department of Electrical and Computer Engineering, University of Florida, Gainesville, FL 32611, USA;3. School of Automation, Hangzhou Dianzi University, Hangzhou 310018, PR China;1. Graduate School of Mechanical and Aerospace Engineering, Gyeongsang National University, 501 Jinjudaero, Jinju 52828, Republic of Korea;2. Department of Electrical Engineering, Hanyang University, 222 Wangsimniro, Seoul 04763, Republic of Korea;1. Medical IT Convergence Research Section, Electronics and Telecommunications Research Institute (ETRI), Daegu 42994, Republic of Korea;2. School of Electronic and Electrical Engineering, Kyungpook National University, Daehak-ro 80, Republic of Korea;3. Smart Mobility Research Section, Electronics and Telecommunications Research Institute (ETRI), Daegu, Republic of Korea;4. Cyber Physical Systems & Control Laboratory, School of Electronic and Electrical Engineering, Kyungpook National University, Daehak-ro 80, Republic of Korea |
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| Abstract: | In the variable speed control momentum gyroscopes (VSCMG), the output torque of the VSCMG can be supported by the gyroscopic torque by a large margin with low resolution. The output torque of the VSCMG can be only supported by the reaction torque of the flywheels with high resolution when the gimbals are locking. Consequently, the torque error that is determined by the low spin rate fluctuation or servo tracking error of the gimbals can be vanished, and the VSCMG can be suitable for large maneuver and high accuracy attitude pointing as the actuator. Unfortunately, the singularity of the flywheel torque co-plane may be encountered. In this paper, the singularity of the flywheel torque co-plane is visualized based on geometry method. The singularity can be effectively avoided by locking gimbals. The locking gimbals positions are optimized with the maximum angular momentum. The steering laws with two phases are proposed to operate the task of the large angle maneuver and high accuracy control for a spacecraft. In the phase 1, a large margin torque can be achieved by the new designed steering law, and the gimbals can be steered to the optimization gimbals positions at the final stage of the phase 1. In the phase 2, the high precision torque can be achieved by only steering the flywheels and the locking the gimbals. Consequently, the torque error that is caused by the spin rate fluctuation or servo tracking error of the gimbals can be effectively eliminated. |
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