Application of a New-type Damping Structure for Vibration Control in Deployment Process of Satellite Antenna Component

Abstract

Abstract Vibration control of flexible deployable mechanism is seriously significant with the increasing application of it in aerospace field. Satellite antenna must be carried out in folded state due to small space of launch vehicle. In the process of deployment and attitude adjustment, vibration has a great influence on the contour accuracy. Based on transfer matrix method, the deployment structure of large flexible deployable satellite antenna is analysed to obtain its natural frequencies and modes. By solving the first three natural frequencies and modes in different deployment angles, the structure completely deployed is prone to be coupled and has the worst stability. Thus, damping structure to suppress vibration at all modal resonance points of fully deployed satellite antenna is necessarily to be installed. A new-type damping structure, multi-petal friction damping structure with the characteristics of simple structure and wide frequency-band, is proposed in previous paper. The dynamic analysis of deployment process at different angles for deployment component with damping structure is carried out to verify the damping effect and the feasibility of damping structure as well as the rationality of theoretical analysis.