Disclosed herein are control systems relating generally to the field of aerodynamics and more particularly to the control of vibration of rotor blades such as helicopter blades. Such systems involve devices for vibration control of each rotor blade, which incorporate control systems of the flow control type (e.g. actively controlled flap) and structural control type (e.g. active pitch link). Also disclosed are related methods of controlling vibration in a rotor blade, wherein the rotor blade is coupled to a rotor hub and has at least a torsional stiffness and a pitch angle associated therewith.