Modelling and stabilization of flexible spacecraft under the influence of orbital perturbation

In this paper the problem of modelling of large flexible spacecraft and their stabilization under the influence of orbital (radial) perturbation is considered. The dynamics of the flexible spacecraft is derived using Hamilton´s principle. The equations of motion consist of a coupled system of ordinary differential equations and partial differential equations. The asymptotic stability of the system is proved using Lyapunov´s approach. Simple feedback controls are suggested for the stabilization of the system. For illustration, numerical simulations are carried out, giving useful results.