An aircraft has a fuselage, and pivot wings pivotally connected with the fuselage, the pivot wings pivoting between a vertical orientation for vertical takeoff, and a horizontal orientation for horizontal flight. Ailerons on each of the pivot wings provide roll control for the aircraft in all phases of flight. A gimbal motor assembly is mounted on the fuselage to adjustably support a motor. An upper rotary pivot free wing is mounted on a mast driven by the motor. A vectored thrust mechanism is provided for forward movement of the aircraft.

A pitch control system configured to vary a pitch angle of at least one of a plurality of propeller blades of a propeller system is provided including a switch movable between a neutral position and a plurality of non-neutral positions. Movement of the switch to a first non-neutral position generates a command to move the propeller blades in a first direction. Movement of the switch to a second non-neutral position generates a command to move the propeller blades in a second direction. Movement of the switch to a third non-neutral position generates a command to move the propeller blades to a zero thrust position.

A pitch control system configured to vary a pitch angle of at least one of a plurality of propeller blades of a propeller system is provided including a switch movable between a neutral position and a plurality of non-neutral positions. Movement of the switch to a first non-neutral position generates a command to move the propeller blades in a first direction. Movement of the switch to a second non-neutral position generates a command to move the propeller blades in a second direction. Movement of the switch to a third non-neutral position generates a command to move the propeller blades to a zero thrust position.

A pitch control system configured to vary a pitch angle of a plurality of propeller blades of a propeller system is provided including a motor having a motor shaft configured to rotate about an axis. A rotary switch having a tab protruding generally outwardly is coupled to the motor shaft and is configured to move between a first position and a second position. The pitch control system also includes a position sensor configured to monitor the position of the rotary switch. The position of the rotary switch is proportional to the pitch angle of the plurality of propeller blades.

A pitch control system configured to vary a pitch angle of a plurality of propeller blades of a propeller system is provided including a motor having a motor shaft configured to rotate about an axis. A rotary switch having a tab protruding generally outwardly is coupled to the motor shaft and is configured to move between a first position and a second position. The pitch control system also includes a position sensor configured to monitor the position of the rotary switch. The position of the rotary switch is proportional to the pitch angle of the plurality of propeller blades.

A rotary wing aircraft includes a fuselage having a plurality of surfaces, at least one engine mounted in the fuselage, and a rotor assembly including a rotor shaft and plurality of rotor blades operatively connected to the rotor shaft. The rotor assembly includes a plurality of surface portions. A rotor shaft fairing extends between the fuselage and the rotor assembly and about at least a portion of the rotor shaft. The rotor shaft fairing includes an outer surface. A plate member is mounted to and projects proudly of the at least a portion of the rotor shaft fairing. The plate member is configured and disposed to increase an aspect ratio of and reduce induced drag on the rotor shaft fairing as well as reduce rotor hub wake size.

A rotary wing aircraft includes a fuselage having a plurality of surfaces, at least one engine mounted in the fuselage, and a rotor assembly including a rotor shaft and plurality of rotor blades operatively connected to the rotor shaft. The rotor assembly includes a plurality of surface portions. A rotor shaft fairing extends between the fuselage and the rotor assembly and about at least a portion of the rotor shaft. The rotor shaft fairing includes an outer surface. A plate member is mounted to and projects proudly of the at least a portion of the rotor shaft fairing. The plate member is configured and disposed to increase an aspect ratio of and reduce induced drag on the rotor shaft fairing as well as reduce rotor hub wake size.

An aircraft assembly is provided and includes a first member extending from an aircraft airframe, a propeller, which is drivable to rotate and a secondary member on which the propeller is supportable and which is aerodynamically pivotable with respect to the first member.

An aircraft assembly is provided and includes a first member extending from an aircraft airframe, a propeller, which is drivable to rotate and a secondary member on which the propeller is supportable and which is aerodynamically pivotable with respect to the first member.

An aircraft includes a plurality of takeoff and landing rotors each generating a first airflow below the takeoff and landing rotor, and a cruise rotor generating a second airflow behind the cruise rotor, the plurality of takeoff and landing rotors including a rear rotor disposed behind the cruise rotor. The aircraft further includes an airflow deflection mechanism capable of changing a direction of the second airflow, and a controller for controlling the airflow deflection mechanism to suppress interference between the first airflow generated by the rear rotor and the second airflow.