Patent ID: 8021116

Claim:
A rotor system for a rotorcraft, comprising: a first pair of rotor blades, comprising: a first rotor blade and a second rotor blade; a first pitch control link operably associated with the first rotor blade; a first coupling link coupled between the first rotor blade to the second rotor blade; wherein actuation of the first pitch control link changes a first pitch setting associated with the first rotor blade and the second rotor blade; a second pair of rotor blades, comprising: a third rotor blade and a fourth rotor blade; a second pitch control link operably associated with the third rotor blade; a second coupling link coupled between the third rotor blade to the fourth rotor blade; wherein actuation of the second pitch control link changes a second pitch setting associated with the third rotor blade and the fourth rotor blade; wherein the first pitch setting is independently controlled by the first pitch control link, while the second pitch setting is independently controlled by the second pitch control link; wherein the first, second, third, and fourth rotor blades are generally in the same plane.