  We consider a mathematical model of an orbiting satellite, comprising a rigid
carrier body and a flexible boom, operating under the influence of gravity
gradient torque. This model is represented by a nonlinear control system, which
includes ordinary differential equations governing the carrier body's angular
velocity and attitude quaternion, coupled with the Euler-Bernoulli equations
that describe the vibration of the flexible component. We propose an explicit
feedback design aimed at guaranteeing the partial stability of the closed-loop
system in an appropriate Hilbert space.
