Patent ID: 8496434

Claim:
A rotor system for a rotorcraft, comprising: a rotor mast; an upper rotor blade and a lower rotor blade, both the upper rotor blade and the lower rotor blade being coupled to the rotor mast so as to rotate about a singular axis of rotation and in a singular direction; and a differential pitch assembly operably associated with the upper rotor blade and the lower rotor blade, so as to control a pitch angle of both the upper rotor blade and the lower rotor blade in tandem; wherein the differential pitch assembly is configured to establish the pitch angle of the upper rotor blade approximately similar to the pitch angle of the lower rotor blade when the rotorcraft is in an airplane mode; wherein the differential pitch assembly is configured to establish the pitch angles of the upper rotor blade and the lower rotor blade such that so that the pitch angle of the upper rotor blade is smaller than the pitch angle of the lower rotor blade when the rotorcraft is in a helicopter mode.