姿控飞轮高速运行时产生的200-300Hz范围内的高频扰动力/力矩是航天器在轨微振动的主要激励源之一。利用动力吸振和干摩擦阻尼耗能，阻尼环在发射段能有效抑制飞轮固有模态的振动放大，但其能否抑制高频扰动是亟待回答的问题。项目针对这一问题，首先建立考虑飞轮实体模型和陀螺效应的飞轮转子动力学模型，分析不平衡激励、轴承不规则激励与飞轮模态的耦合作用，揭示扰动生成机理和飞轮模态特征；然后建立弹性支承阻尼环-干摩擦界面-飞轮的非线性多自由度等效模型和有限元缩聚动力学模型，先不考虑激励，进行复非线性模态分析，明确干摩擦阻尼对模态参数、系统稳定性的影响规律；进而求解各可能激励下的响应，获得扰动响应和干摩擦界面局部动力学行为特征，明确阻尼环和摩擦界面设计参数对扰动抑制的影响规律，指导阻尼环的优化设计。开展模态测试和飞轮运行时的扰动力/力矩测试，验证相关机理和效果，为飞轮高频扰动控制提供理论依据和技术支撑。

For attitude control flywheels operating at high rotational speed, the disturbance force/moment in the high frequency range 200-300Hz is one of the main vibration sources for on-orbit mircovibrations of spacecraft. By employing the mechanisms of dynamic vibration absorber and dry friction damping to dissipate energy, friction rings can effectively suppress the vibration and shock responses of flywheels in the launching phase. However, whether the friction rings can reduce the high-frequency disturbance force/moment or not is still a problem to be answered. Aimed at the problem, three aspects are considered to be investigated. Firstly, taking gyroscopic effect into consideration, establish the dynamic models of the flywheel to analyze the interaction between the poly-harmonic disturbances of mass imbalance or bearing irregularity and the structural modes, determine the mechanism of generating the high-frequency disturbance and the structural modes to be suppressed. Then, establish the nonlinear multi-degrees-of-freedom dynamic model and the nonlinear reduced finite element model of the friction rings with dry friction interfaces 饿elastically mounted on a flexible flywheel. On the one hand, without considering excitation forces, carry out complex nonlinear modal analysis to highlight the effects of dry friction damping on nonlinear modal parameters and system stability; on the other hand, conduct the solution under possible excitations to obtain the disturbance force/moment and study the local behavior of dry friction interfaces, carry out parameter analysis on design parameters of friction rings and the interfaces, clarify the influence of these parameters on disturbance force/moment suppression. Modal tests and disturbance tests on Kistler Table measurement system are carried out to verify theoretical findings and effectiveness. The investigation will provide theoretical basis and technical support for high-frequency disturbance suppression of attitude control flywheels.