Control moment gyroscope is a commonly used controller in an attitude control system of spacecraft. Control methods research of control moment gyroscope can provide necessary theoretical basis for developing attitude control system of spacecraft. In this paper, three control laws for control moment gyroscope by successive loop closure/PD, pole placement, full state feedback linear quadratic regulator, are designed respectively, and the validity of the three methods are confirmed by controlling an actual system to meet the expected control target. The control performances of the methods are compared and analyzed, and the results of the three control strategies have provided theoretical guidance for further studies in this system.%大型航天器姿态控制系统通常采用控制力矩陀螺作为其执行机构.控制力矩陀螺控制方法研究将为航天器姿态控制提供必要的理论基础.本文针对控制力矩陀螺系统,分别采用连续闭环PD控制、极点配置、全状态反馈线性二次型3种控制方法,对控制力矩陀螺进行控制律设计,对实际系统进行有效控制,使其满足期望的控制指标,对3种方法的控制性能进行了比较分析,深化了对控制方法的理解,并且对控制力矩陀螺的研究具有理论指导意义.
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