快速机动小卫星执行机构研究

Research on momentum management of fast slew maneuver small satellite

为了验证采用控制力矩陀螺作为小卫星的姿态控制执行部件,大幅提升小卫星机动能力的可行性,根据控制力矩陀螺的工作原理,设计了控制力矩陀螺原理样机,并利用单轴气浮转台进行了控制力矩陀螺半物理仿真实验。实验结果表明,控制力矩陀螺作为小卫星执行机构,可使小卫星在8 s内机动20°,机动速度可达2.5°/s,实现了在短时间内完成小卫星大角度快速机动和入轨后快速定姿,为控制力矩陀螺在小卫星上的实际工程应用提供了依据。

In order to validate the feasibility of improving the small satellite＇s maneuvering performance by adopting Control Moment Gyro（CMG） as its executive component for attitude control,a single Gimbol CMG（SGCMG） prototype was designed on the basic theory of the SGCMG, and a SGCMG hardware-in-loop simulation experiment was completed. The results indicate that the small satellite maneuver can achieve by 20^o in 8 s, and the maneuver velocity can get to 2.5 ^o/s by using the SGCMG to control small satellite attitude. The research provide an evidence for practical application of CMG on small satellites.