Abstract: A rotorcraft rotor head has: (i) two or more rotor blades attached to rotate about a rotor axis, and pivot through a flapping and/or teetering hinge, and having a pitch angle; (ii) pitch angle changing means for collectively changing said pitch angle; (iii) centrifugal pitch stop mechanism having an activation point and comprising one or more centrifugal plates; and (iv) control means for providing a control input to said pitch angle changing means; wherein said centrifugal pitch stop mechanism is configured to attain an activated state and to interact with said pitch angle changing means; wherein said activated state is attained when the rotational speed of said rotor blades is greater than said activation point and when a control input is provided by said control means; and wherein said activation point is less than the minimum rotational speed of the rotor blades that is required for flying the rotorcraft.