Patent ID: 9604729
Date: 2017-03-28
CPC Classifications: B64C,B64D

Claim:
1. A method of controlling an aircraft comprising: rotating a first rotor operatively coupled to a propeller shaft assembly in a first direction; rotating a second rotor operatively coupled to the propeller shaft assembly in a second direction that is opposite of the first direction, wherein the first rotor and the second rotor are rotated proximate a fixed wing of the aircraft about a common axis extending parallel to a longitudinal axis of the aircraft; maintaining a first plurality of blades mounted to the first rotor at a substantially identical nominal pitch during rotation of the first rotor; cyclically changing the pitch of a second plurality of blades mounted to the second rotor during rotation of the second rotor; and generating a moment upon cyclically changing the pitch of the second plurality of blades to control the aircraft.