  The derivation of a linear fractional representation (LFR) model for a
flexible, spinning and uniform Euler-Bernoulli beam is accomplished using the
{Lagrange} technique, fully capturing the centrifugal force generated by the
spinning motion and accounting for its dependence on the angular velocity. This
six degrees of freedom (DOF) model accounts for the behavior of deflection in
the moving body frame, encompassing the bending, traction and torsion dynamics.
The model is also designed to be compliant with the Two-Input-Two-Output Port
(TITOP) approach, which offers the possibility to model complex multibody
mechanical systems, while keeping the uncertain nature of the plant and
condensing all the possible mechanical configurations in a single LFR. To
evaluate the effectiveness of the model, various scenarios are considered and
their results are tabulated. These scenarios include uniform beams with fixed
root boundary conditions for different values of tip mass, root offset and
angular velocity. The results from the analysis of the uniform cantilever beam
are compared with solutions found in the literature and obtained from a
commercial finite element software. Ultimately, this paper presents a multibody
model for a spinning spacecraft mission scenario. A comprehensive analysis of
the system dynamics is conducted, providing insights into the behavior of the
spacecraft under spinning conditions.
