为了研究高分辨率光学卫星星上飞轮的微振动对卫星成像质量的影响，分别建立了飞轮扰动模型和整星结构动力学模型。 首先，对飞轮组件系统进行了地面扰动测试，对实测扰动数据的分析表明，飞轮组件在与转速相关的一阶频率50 Hz处产生一次谐波，在190 Hz与280 Hz左右存在与转速无关的一系列峰值。然后，对整星进行了单位正弦激励，获得了光轴角位移响应，并对其与飞轮实测扰动数据进行了集成分析。分析结果表明: 整星在50~80 Hz和230~280 Hz的角位移响应有较多的谐振响应频率成分，沿光轴方向和垂直光轴方向整星光轴的角位移最大谐振响应幅值分别为2.718″、2.739″，在245 Hz左右存在较多幅值为0.5″量级的谐波。分析显示飞轮组件微振动对高分辨率光学卫星成像质量影响较大，得到的结果可为整星系统的优化设计和隔振补偿措施提供参考依据。

To explore the influence of micro-vibration of flywheel components on the imaging quality of a high resolution optical satellite, a flywheel component disturbance model and a whole structure dynamic model of the satellite were established. The ground disturbance of flywheel components was tested, the analysis of the measured data shows that there is series of first harmonics at the first order frequency 50 Hz, and a series of peaks independent on rotation speeds around the 190 Hz and 280 Hz. Then, the unit sine excitation was performed on the satellite, the angular displacement response of the optical axis was obtained. The integration of the angular displacement response and the flywheel measured disturbance data was analyzed. The results show that there are a lot of angular displacement harmonic response frequencies in 50 Hz-80 Hz and 230 Hz-280 Hz, the maximum angular displacement resonance amplitudes are 2.718″ and 2.739″ along the optical axis direction and the vertical direction, and 0.5″ magnitude harmonic amplitude is around 245 Hz. It concludes that the flywheel micro vibration has a great influence on the imaging quality of high resolution optical satellites and the results provide important references for system optimum design and vibration isolation.