Dynamic Modeling and Stability Analysis of a Control Moment Gyroscope Considering the Influence of a Flexible Vibration Isolator

Microvibrations of spacecraft are mainly generated by control moment gyroscopes (CMGs), which seriously reduces the effectiveness of spacecraft attitude control. Considerable work about vibration isolators has been conducted for isolating microvibrations generated from CMGs and minimize their effect. However, deformations of isolators are coupled with the motion of CMGs, which influences the output performances. We focus on identifying how the vibration of dynamic and isolator parameters affect the output characteristics of a CMG with an isolator. A theoretical model is established and the coupling principle of the CMG-isolator system is described systematically. We verify the numerical simulation using MATLAB/Simulink software, analyze the stability of this model and estimate the domain of attraction by Monte Carlo method. Finally, an SGCMG-isolator prototype is fabricated and an integrated test system is assembled to get properties of the prototype; a series of confirmatory experiments are designed and conducted. Model correction is verified via a comparison of the numerical and experimental data.