Spacecraft Vibration Control Based on Extended Modal Decoupling of Vernier-Gimballing Magnetically Suspension Flywheels

Abstract

Aimed at solving the microvibration issue of spacecraft, this paper adopts two orthogonal Vernier-gimballing magnetically suspended flywheels (VGMSFs) as vibration suppression actuator. The vibration decoupling control law and Vernier-gimballing steering law of the VGMSFs is designed to output the translational and rotational reference displacements of the VGMSFs. By extending the traditional modal decoupling of the magnetically suspended rotor, the on-orbit nonlinear VGMSF system coupled with satellite realizes the precise modal separation and rotation mode decoupling. This method not only realizes complete compensation for the disturbance torque from spacecraft to VGMSFs, but also improves the decoupling precision of Vernier-gimballing moment of VGMSFs. Most importantly, through independent control of translation and rotational modes of on-orbit VGMSFs, the parameter regulation range of spacecraft vibration decoupling controller is greatly enlarged, effectively improving the microvibration suppression effect of spacecraft. The semiphysical simulation results testify the effectiveness and superiority of this method.