Analysis of the kinematics and dynamics of a helicopter main rotor is presented in the paper. A rigid rotor type is assumed, where feathering angle of the blade is controlled by a swashplate mechanism. Kinematic constrains and links equilibrium are studied in order to determine the mechanism movement and the forces on the servoactuators which drive the swashplate position and orientation. The modeling presented is intended to be part of a simulation platform to evaluate fly-by-wire actuation systems performances applied to helicopter main rotors control.

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