Nonlinear forced vibration analysis of aircraft wings with rotating unbalanced mass of the propeller system

In this paper, the aeroelastic response of a wing containing a propeller system with rotating unbalanced mass is presented. Nonlinear structural model of the wing carrying a propeller system is extracted and coupled with an incompressible unsteady aerodynamic model. The governing equations and boundary conditions are determined via Hamilton’s variational principle. Galerkin’s approach is used to transfer the resulting partial differential equation into ordinary nonlinear differential equations. Using the method of multiple scales, frequency response function of the system in different primary resonance cases is obtained analytically and the flutter occurrence possibility in each case is investigated. According to the results, jump phenomenon can be observed in each two primary resonance cases. Also, for the case of non-resonant excitation, the stability of the system is independent of the rotating unbalanced mass parameter.