Gyroscopic effects on the engine rotor on the characteristics of wing bending-torsional flutter

Abstract Bending-torsional flutter equations of a wing-engine system have been derived, taking into account of the gyroscopic effects of the engine rotor on the wing structure. The connection between the wing and the engine was assumed to be stiff in the equation. Flutter characteristics of the wing with gyroscopic effect was analyzed. The results showed that, with the stiffness of the pylon ignored, the gyroscopic moment raised the flutter speed and flutter frequency of the system, whilst it didn′t affect the inherent flutter mechanism. As a result, the gyroscopic effect on the flutter of the wingengine system could be effectively modeled as a system damping, and the equivalent damping ratio rose with the rotational speed of the engine.