Patent ID: 8636473

Claim:
A rotor system for a rotorcraft, comprising: a rotor blade pair comprising an upper rotor blade and a lower rotor blade; a differential pitch assembly operably associated with the rotor blade pair for controlling a pitch angle of the upper rotor blade and the lower rotor blade, the differential pitch assembly comprising: a swashplate link coupled between a swashplate and a lower pitch horn; an intermediate link coupled between an upper pitch horn and the lower pitch horn; wherein the upper rotor blade is coupled to the upper pitch horn; wherein the lower rotor blade is coupled to the lower pitch horn; whereby actuation of the swashplate link changes the pitch of both the upper rotor blade and the lower rotor blade; wherein the upper rotor blade and the lower rotor blade both rotate in a single direction and about a same axis of rotation; wherein the upper rotor blade and the lower rotor blade are configured to provide a propulsive force upon the aircraft; whereby actuation of the swashplate link changes the pitch of the upper rotor blade more severely than the pitch of the lower rotor blade.