DYNAMIC MODEL OF THREE JOINTS HELICOPTER ROTOR WITH CONSIDERING NONLINEAR UNSTEADY AERODYNAMICS

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Abstract

This paper presents the general equations describes helicopter rotor dynamics with a full range of typical motions including flapping, lagging and rotating. Here, the aerodynamic properties of the rotor are considered to be nonlinear, unsteady, taken from the model calculated by the discrete vortex method. A numerical simulation was performed to solve the differential equations of these nonlinear motions at steady-state conditions, thereby determining the position responses of the blades.