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Abstract
This thesis details the coupling of the rigid body parallel kinematics of an articulated rotor hub with a nonlinearly elastic rotor blade to provide vibration control to the fuselage and cockpit of the rotorcraft. A model rotor hub is examined, with distinction made between the aerodynamic load path and control load path, to complete the dynamic model. An examination of vibration suppression by replacing the standard pitch link in the control kinematic chain with an adaptive pitch link, suitable for vibration attenuation, is included. The mathematical basis for the elastic and rigid body elements of the simulation is described in detail. Computer simulations show the accuracy and validation of the constructed dynamic model, with a brief examination of control objectives succeeding.
