Modelling of flexible spacecraft and their stabilization?

The paper deals with the problem of rigorous modelling of flexible spacecraft and their stabilization. The attitude dynamics of the satellite bus and the equations for vibration of a flexible beam attached to it are derived. The complete system dynamics are given by a coupled set of ordinary and partial differential equations. The effects of controls applied on the. bus and/or on the flexible beam are investigated. It is shown that stabilization of the flexible spacecraft can be achieved by use of simple feedback controls.