飞轮被动减振卫星动力学建模及稳定性研究

为提高卫星的指向精度和稳定度,通常在飞轮系统中设计了被动减振器。而对于有敏捷机动要求的卫星,被动减振器的低刚度设计可能会破坏姿态控制系统的动态性能和稳定性。因此,针对飞轮减振情况,建立了卫星刚柔姿态动力学方程,用来准确分析卫星敏捷机动时的动态性能、稳定性问题以及飞轮扰动对卫星稳定度的影响。仿真结果表明,不合适的隔振器刚度设计将会影响指向的动态性能和稳定性,甚至诱发姿控系统失稳。

Modeling and stability research on satellite dynamics with passive vibration isolation of flywheel

To improve the pointing accuracy and stability of satellites,passive isolators are usually designed for flywheel systems.But for satellites with agile maneuvering requirements,the low stiffness design of passive isolators may destroy the transient performance and stability of the attitude control system.Therefore,in this paper,the rigid-flexible attitude dynamics equation of satellites is established for flywheels vibration.The proposed equation is used to analyze the transient performance and stability problem of the agile maneuver and the passive isolators are used for flywheel disturbance on satellite stability.Simulation results show that the improper stiffness design of the isolator affects the pointing transient performance and stability,even results in a unstable attitude control system.