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We consider a mathematical model of an orbiting satellite, comprising a rigidcarrier body and a flexible boom, operating under the influence of gravitygradient torque. This model is represented by a nonlinear control system, whichincludes ordinary differential equations governing the carrier body's angularvelocity and attitude quaternion, coupled with the Euler-Bernoulli equationsthat describe the vibration of the flexible component. We propose an explicitfeedback design aimed at guaranteeing the partial stability of the closed-loopsystem in an appropriate Hilbert space.

Partial Stabilization of an Orbiting Satellite Model with a Flexible Attachment