A blade pitch adjustment mechanism includes a pitch cylinder having a first face and pitch slots extending longitudinally from the first face, a blade sleeve having a second face and a blade slot extending longitudinally from the second face, the blade sleeve is configured to be rotationally positioned in the pitch cylinder with the second face located with the first face, wherein the blade slot and the pitch slots are cooperative to form keyway, corresponding to a discrete blade pitch, when the blade slot is aligned with a pitch slot.

An anti-torque rotor is described that comprises: a mast rotatable about a first axis; a plurality of blades extending along respective second axes; a control element sliding along the first axis with respect to the mast, integrally rotatable with said mast, and connected to said blades; a control rod sliding axially along first axis and angularly fixed with respect to said first axis; a connection element interposed between the control rod and the control element, sliding along the first axis integrally with the control rod, and configured to enable the relative rotation of said control element with respect to the control rod about the first axis; and a transmission unit available in an active configuration or an inactive configuration; the transmission unit, in turn, comprises: an annular ridge axially and angularly integral with the control rod and radially projecting from the control rod; and a seat engaged by the ridge and angularly integral with the control element.

An anti-torque rotor is described that comprises: a mast rotatable about a first axis; a plurality of blades extending along respective second axes; a control element sliding along the first axis with respect to the mast, integrally rotatable with said mast, and connected to said blades; a control rod sliding axially along first axis and angularly fixed with respect to said first axis; a connection element interposed between the control rod and the control element, sliding along the first axis integrally with the control rod, and configured to enable the relative rotation of said control element with respect to the control rod about the first axis; and a transmission unit available in an active configuration or an inactive configuration; the transmission unit, in turn, comprises: an annular ridge axially and angularly integral with the control rod and radially projecting from the control rod; and a seat engaged by the ridge and angularly integral with the control element.

An aircraft is provide including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. At least one flight control computer configured to independently control the upper rotor assembly and the lower rotor assembly through a fly-by-wire control system. A plurality of sensors to detect sensor data of at least one environmental condition and at least one aircraft state data, wherein the sensors provide the sensor data to the flight control computer.

An aircraft is provide including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. At least one flight control computer configured to independently control the upper rotor assembly and the lower rotor assembly through a fly-by-wire control system. A plurality of sensors to detect sensor data of at least one environmental condition and at least one aircraft state data, wherein the sensors provide the sensor data to the flight control computer.

A blade pitch adjustment mechanism includes a pitch cylinder having a first face and pitch slots extending longitudinally from the first face, a blade sleeve having a second face and a blade slot extending longitudinally from the second face, the blade sleeve is configured to be rotationally positioned in the pitch cylinder with the second face located with the first face, wherein the blade slot and the pitch slots are cooperative to form keyway, corresponding to a discrete blade pitch, when the blade slot is aligned with a pitch slot.

A pitch beam movable by a pitch change shaft to adjust a pitch of at least one rotor blade of a rotor system via a pitch linkage includes a first surface having a generally planar configuration, a smooth second surface disposed opposite the first surface, and a sidewall extending between the first surface and the second surface. A pitch linkage connection point is disposed at the sidewall to which the pitch linkage is attachable. An interior is defined between the first surface and the second surface and an opening extends through the first and second surface at a rotational axis of the rotor system to which the pitch change shaft is attached. Movement of the pitch change shaft moves the pitch beam and adjusts the pitch of the at least one rotor blade via the pitch linkage attached at the pitch linkage connection point.

A pitch beam movable by a pitch change shaft to adjust a pitch of at least one rotor blade of a rotor system via a pitch linkage includes a first surface having a generally planar configuration, a smooth second surface disposed opposite the first surface, and a sidewall extending between the first surface and the second surface. A pitch linkage connection point is disposed at the sidewall to which the pitch linkage is attachable. An interior is defined between the first surface and the second surface and an opening extends through the first and second surface at a rotational axis of the rotor system to which the pitch change shaft is attached. Movement of the pitch change shaft moves the pitch beam and adjusts the pitch of the at least one rotor blade via the pitch linkage attached at the pitch linkage connection point.

An active flow control system for generating yaw control moments for an aircraft during hover flight. The system includes right and left yaw effectors disposed proximate the right and left wingtips of the wing. A pressurized air system includes a pressurized air source and a plurality of injectors operably associated with the right and left yaw effectors. Based upon which of the injectors is injecting pressurized air, the right and left yaw effectors generate no yaw control moment, generate a yaw right control moment or generate a yaw left control moment.

An active flow control system for generating yaw control moments for an aircraft during hover flight. The system includes right and left yaw effectors disposed proximate the right and left wingtips of the wing. A pressurized air system includes a pressurized air source and a plurality of injectors operably associated with the right and left yaw effectors. Based upon which of the injectors is injecting pressurized air, the right and left yaw effectors generate no yaw control moment, generate a yaw right control moment or generate a yaw left control moment.