Abstract: An improved aircraft design to harness advantages of vertical or short-takeoff and landings (V/STOL) and efficient horizontal flight is disclosed. The aircraft design includes multiple thrust sources and wings which are free to rotate on a spanwise axis, and have their center of gravity aft of the axis of rotation. Wing rotation is decoupled from both the fuselage and the thrust sources. Wings are coupled to each other such that rotation induced in one wing affects rotation in all wings. Thrust sources are directed vertically during hover and some degree forward of vertical for horizontal flight. The disclosed configuration improves aircraft flight stability and efficiency in all flight profiles: vertical flight, transition to/from horizontal flight, and horizontal flight. The aircraft has the possibility of a controlled emergency landing using autorotation of the propellers, wings or a combination of the two.

Abstract: An improved aircraft design to harness advantages of vertical or short-takeoff and landings (V/STOL) and efficient horizontal flight. Configuration improves aircraft flight stability and efficiency in flight profiles: (1.) vertical flight; (2.) transition to and from horizontal flight and; (3.) horizontal flight on wings. The aircraft is capable of stable flight at any airspeed from hover to its maximum designed speed. It has the possibility of a controlled emergency landing using autorotation or, wings or, a combination of the two. Aircraft design includes: multiple thrust sources and, wings free to rotate on a spanwise axis. Wing rotation is independent—not coupled—with either the fuselage or, the thrust sources. Wing configurations include single, tandem or, multiple sets. Wings are coupled each other such that rotation induced in one wing affects rotation in all wings. Thrust sources are directed vertically during hover and some degree forward of vertical for horizontal flight.