Dynamic features analysis and reliability study of whole-spacecraft vibration isolation

Abstract

The viscoelastic material in vibration control is widely studied. The dynamic environment of spacecraft can be improved by whole-spacecraft vibration isolation during launch. The traditional solution of improving the dynamic environment of structure is to increase the area of viscoelastic material. In the paper, the problems of reliability and vibration isolation effect, which are focused by the designers, are dissused. By the reliability method, the dynamic model of coupled system is also studied. The natural frequencies and damping feature problems which are affected by the stiffness of viscoelastic material are dissussed by the dynamic model of coupled system. Furthermore, the stiffness of viscoelastic material is simplified to the structural damping. By both the computation result and the experiment data, it is demonstrated that raising the stiffness of viscoelastic material cannot raise the modal loss factor of system accordingly.