Abstract: The present application includes a main rotor assembly for an aircraft. The rotor assembly has a main rotor mast configured for rotation about a mast axis and two yokes pivotally connected to the mast for rotation therewith about the mast axis. Each yoke is independently pivotable relative to the mast about at least one flap axis that is generally perpendicular to the mast axis. In at least one embodiment, a torque splitter connects the yokes and allows for limited rotation of the yokes relative to each other about the mast axis. Each yoke is configured for the attachment of rotor blades extending generally radially relative to the mast axis.

Abstract: According to one embodiment, a rotorcraft includes a main rotor system, an anti-torque rotor system, an anti-torque rotor enhancement system, and an anti-torque rudder system. The anti-torque rotor enhancement system includes an aerodynamic structure having an opening therethrough and a support structure coupling the aerodynamic structure to the body of the rotorcraft such that the opening is positioned proximate to a rotation path of the at least one anti-torque rotor blade. The anti-torque rudder system includes at least one rudder surface operable to provide a second force on the body in the direction of rotation of the at least one main rotor blade.

Abstract: The present application includes a main rotor assembly for an aircraft. The rotor assembly has a main rotor mast configured for rotation about a mast axis and two yokes pivotally connected to the mast for rotation therewith about the mast axis. Each yoke is independently pivotable relative to the mast about at least one flap axis that is generally perpendicular to the mast axis. In at least one embodiment, a torque splitter connects the yokes and allows for limited rotation of the yokes relative to each other about the mast axis. Each yoke is configured for the attachment of rotor blades extending generally radially relative to the mast axis.

Abstract: An aircraft includes a surface over which an airflow passes. A plasma actuator is configured to generate a plasma above the surface, the plasma coupling a directed momentum into the air surrounding the surface to reduce separation of the airflow from the surface. A method of reducing separation of an airflow from a surface of an aircraft includes generating a plasma in air surrounding the surface at a position where the airflow would separate from the surface in the absence of the plasma.

Abstract: An aircraft includes a surface over which an airflow passes. A plasma actuator is configured to generate a plasma above the surface, the plasma coupling a directed momentum into the air surrounding the surface to reduce separation of the airflow from the surface. A method of reducing separation of an airflow from a surface of an aircraft includes generating a plasma in air surrounding the surface at a position where the airflow would separate from the surface in the absence of the plasma.

Abstract: An apparatus for interconnection in a helicopter tail rotor control linkage for changing the pitch of the tail rotor blades in response to predetermined inputs is provided. The apparatus comprises a linkage member having a variable geometry, an actuator, and a control unit. In a preferred embodiment, the control unit utilizes a microcontroller to monitor inputs corresponding to ambient air condition and automatically vary the maximum tail rotor pitch so as to provide maximum tail rotor authority over a range of altitudes.

Abstract: Nozzles for discharging high velocity air are positioned on either side of an aircraft engine exhaust duct exit. High velocity air is discharged tangential to an outer surface of each nozzle and follows the contour thereof. The nozzles are positioned so that when the high velocity air separates from the outer surface of the respective nozzles, it flows outwardly relative to the aircraft's fuselage structure. The high velocity air from the nozzle closest to the aircraft's fuselage structure impinges on the exhaust gas stream, deflecting the stream away from the fuselage. The high velocity air from the nozzle furthest from the fuselage creates a low pressure area which deflects the exhaust gas stream away from the fuselage. In combination, the two nozzles deflect the exhaust gas stream away from the fuselage to a significant degree.