The multi-target rapid maneuver control problem is studied for agile satellites with Variable Speed Control Moment Gyro(VSCMG) as actuator.
研究了以变速控制力矩陀螺（VSCMG）作为执行机构的卫星多目标快速机动的控制问题。
The attitude dynamic equation of a spacecraft with VSCMG attached and a global asymptotical attitude feedback control law are presented firstly.
首先建立了以变速控制力矩陀螺为执行机构的航天器姿态动力学模型，并给出了全局稳定的姿态反馈控制律。
This research is focused on the singularity analysis for single-gimbal control moment gyros systems (SCMGs) which include two types, with constant speed (CSCMG) or variable speed (VSCMG) rotors.
使用几何方法对单框架控制力矩陀螺群（包括转子恒速的CSCMG和转子变速的VSCMG）的奇异性进行了分析。
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