An aircraft mock-up for ground testing is modeled as shown, where a brace
represented as a torsional spring of stiffness \(k_{T}\) has been attached at
the pivot support to restrain excessive yawing. It is assumed that during a
test, both thrusters will exert a constant force of magnitude \(F_{0}\).
However, during a simulation, one of the thrusters deviates from the
prescribed force by adding a perturbation in the form of a harmonic thrust of
small amplitude. Thus, the force applied by this thruster takes the form
\(F(t)=F_{0}(1+\varepsilon \sin \Omega t)\), as indicated, where \(\varepsilon
\ll 1\). Determine the steady state yawing motion of the mock-up. What is the
amplitude of the response at resonance?