Patent ID: 8424798
Filing Date: 2013-04-23
Classification: B64C

Abstract:
1. is amended as follows: An aircraft comprising: a fuselage having a front end and a longitudinal axis; a main helicopter rotor supported for rotation about an axis thereof on top of the fuselage, said rotor being operable to control both vertical and horizontal movement of the aircraft; a powerplant supported on the fuselage and operatively connected to the main helicopter rotor for driven rotation thereof in a direction causing blades of the main helicopter rotor to retreat rearwardly away from the front end of the fuselage on a first side of the fuselage; a thrust generator supported on the fuselage and operable to selectively product thrust to move the aircraft forward; a primary wing configuration supported on the fuselage and projecting laterally outward relative thereto to counter dissymmetry of lift of the main helicopter rotor during forward flight by producing more wing-generated lift on the first side of the fuselage than on a second side thereopposite, and a tail assembly that comprises a tail boom extending rearward from the fuselage and a tail structure extending laterally from the tail boom at a distance rearward from the fuselage, the tail structure being configured to produce more drag on one side of the tail boom than another, the one side of the tail boom on which more drag is provided by the tail structure being opposite the first side of the fuselage.