Nonlinear Aeroelastic Characteristics of a Supersonic All-Movable Fin with Single or Multiple Freeplay Nonlinearities

Establishing the aeroelastic characteristic of all-movable fins with freeplay nonlinearities is one most common problems in design supersonic flight vehicles. In this context, study provided novel points view on nonlinear characteristics an fin its root. The unsteady aerodynamic model that was employed uses second-order piston theory considering thickness effects. For a system multiple nonlinearities, discrete scanning method based describing function established to solve limit-cycle oscillations (LCOs) and avoid loss solutions. Combining time-domain integration method, influences support stiffness at root size ratio bending torsional degrees freedom dynamical response were analyzed. results demonstrate systems single nonlinearity exhibit two completely different types LCO, while complex behaviors such as LCO quasi-periodic chaotic motions. path torus breaking into chaos observed. Furthermore, harmonic initial condition for proposed; can be used quick check frequency-domain calculation results.