控制力矩陀螺(CMG)的振动干扰会对航天器姿态控制精度和稳定度产生不利的影响, 目前尚缺乏有效的方法对其进行数学建模及分析。本文根据CMG系统中高速转子和低速组件两部分结构差异较大、难以用统一的方法进行数学建模的特点, 提出了一种将解析建模和试验辨识相结合的系统建模方法来研究CMG的干扰传递模型, 并进行了试验验证。试验结果表明: 本文所建立的干扰传递模型准确无误, 同时验证了“高速转子的不平衡振动是CMG高频抖动产生的主要源头”这一重要结论。

The vibration disturbance generated by Control Moment Gyro (CMG) has adverse effects on precision and stability of the attitude control system in spacecraft and there is still lack of effective methods to conduct mathematic modeling and analysis on it. Due that there is large structure difference between high-speed rotors and low-speed components of CMG, and it is hard to make mathematic modeling with unified methods, a system modeling method combined analytical modeling with test identification was established in the article to study the disturbance transmission mode of CMG, and an experiments was conducted to verify it. The results show that the disturbance transmission model proposed is correct and able to verify the conclusion that “unbalance vibration of high speed rotor is the main disturbance resource in CMG”.