Patent ID: 8469307

Claim:
A rotary wing aircraft comprising: an airframe for supporting a plurality of rotor systems for rotation about a common axis of rotation; a first rotor system of the plurality of rotor systems, the first rotor system including first variable pitch rotor blades supported for rotation about the common rotor axis of rotation in a first rotor plane of rotation and a first pitch controller for controlling the pitch of the first rotor blades; a second rotor system of the plurality of rotor systems, the second rotor system including second variable pitch rotor blades supported for rotation about the common rotor axis of rotation in a second rotor plane of rotation and a second blade pitch controller for controlling the pitch of the second rotor blades; a first pitch control linkage located between the first rotor plane of rotation and the second rotor plane of rotation having a first end coupled to the first blade pitch controller and a second end coupled to the second blade pitch controller; wherein displacement of the first pitch control linkage operates both the first blade pitch controller and second blade pitch controller simultaneously; further including a first servo actuator for operating the first pitch linkage; and wherein the first servo actuator is located between the first rotor plane of rotation and second rotor plane of rotation.