The behaviour of large and flexible space structures, if compared with compact and rigid ones, is largely influenced by thermal loads in orbit. In this paper, the control of a spacecraft attitude disturbance, induced by cyclic temperature variations in the solar array substructures, is investigated. Both passive and active control techniques have been considered to reduce the vibration amplitude. A new version of tension mechansim powered by constant force springs is compared with a previous mechanism from the point of view of induced disturbances in the satellite attitude. A new algorithm for closed-loop pole placement of a symmetric, second order dynamical system is presented, and results of closed-loop numerical simulations are shown. Finally, experimental investigations are discussed and the relative results are presented.