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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 of control moment gyroscope (CMG) can adversely affect the attitude control accuracy and stability of spacecraft. At present, there is no effective method to do mathematical modeling and analysis. In this paper, according to CMG system, the two parts structure of high-speed rotor and low-speed components are quite different and it is difficult to use the uniform method to make mathematical modeling. A system modeling method based on analytical modeling and experimental identification is proposed to study CMG The model of interference transmission was tested and verified. The experimental results show that the disturbance transfer model established in this paper is accurate, and the important conclusion is that “the unbalance vibration of high-speed rotor is the main source of CMG dithering”.