摘要
提出一种基于磁悬浮控制力矩陀螺(magnetically suspended control moment gyroscope,MSCMG)金字塔构型的航天器姿态测控一体化控制方法,利用姿控回路中的执行机构,既进行航天器姿态测量,又进行航天器姿态控制,改变了传统姿控系统由姿态敏感器、控制器、执行机构的组成方式。首先建立磁悬浮转子径向力矩模型,通过实时检测磁悬浮控制力矩陀螺中的磁轴承电流、磁悬浮转子位移、框架角速度,联立金字塔构型中的3个径向力矩模型求解出航天器的姿态角速度,再设计相应的姿态控制律和框架操纵律,实现航天器的姿态调节,仿真结果证明了该方法的正确性和有效性。
A measurement and control integrated method of spacecraft attitude based on magnetically suspended control moment gyroscope（MSCMG）of pyramid configuration is proposed.The actuator in attitude control loop is used to measure and control spacecraft attitude,thus breaking the traditional attitude control loop which is composed by attitude sensor,controller,actuator.The radial torque model of the magnetic suspension rotor is established firstly,real-time detect magnetic bearing current,magnetic suspension rotor displacement and the frame angular velocity in MSCMG,get spacecraft attitude angular velocity through simultaneous three radial torque model in pyramid configuration.Then the control law of attitude and steering law of framework is designed to realize spacecraft attitude regulation.The simulation results show the effectiveness and superiority of this method.
出处
《系统工程与电子技术》
EI
CSCD
北大核心
2016年第1期123-129,共7页
Systems Engineering and Electronics
基金
国家自然科学基金(51475472
61403396)资助课题
关键词
磁悬浮控制力矩陀螺
转子径向力矩模型
金字塔构型
测控一体化
magnetically suspended control moment gyroscope（MSCMG）
radial torque model of magnetic suspension rotor
pyramid configuration
measurement and control integrated method
