Author(s)

M. Pascal

Abstract

The subject of this work is the dynamics of a flexible space station modelled by a main rigid body connected to several flexible appendages. The aim of this investigation is the modal analysis of the system assuming that the spacecraft is gravity gradient stabilized and revolves around the Earth in a circular orbit. A concrete model of space station is more particularly investigated : the system consists of a main rigid body (BJ connected to two large flexible solar pannels. For each flexible appendage, some particular vibrations modes (rotating base cantilever eigen functions) are defined by an exact continuum method. The modal analysis of the coupled system is performed by assuming that the deformations of each flexible appendages a

Keywords