Bending-torsional vibrations of aircraft wing

The problems of bending-torsional flutter an aircraft wing are considered. Using equations motion by the Bubnov-Galerkin method, based on polynomial approximation deflections and angle twist, problem is reduced to studying a system ordinary integro-differential equations, where independent variable time. solution with singular kernels found numerical method quadrature formulas. influence physical-mechanical geometric parameters was studied. It established that account for viscoelastic properties material thin-walled structures leads 40-60% decrease in critical velocity. shown increase elongation parameter