Yaw control system for vtol tilt wing aircraft

Claim 1

A TILT-WING TYPE VTOL AIRCRAFT WHICH INCLUDES A FUSELAGE, SELECTIVELY ORIENTABLE WING STRUCTURE EXTENDING TRANSVERSELY OF SAID FUSELAGE WHICH IS PIVOTAL RELATIVE THERETO BETWEEN A FIRST GENERALLY HORIZONTAL POSITION IN WHICH THE PLANE OF SAID WING STRUCTURE IS GENERALLY PARALLEL TO THE LONGITUDINAL AXIS OF SAID FUSELAGE AND A SECOND GENERALLY UPRIGHT POSITION IN WHICH THE PLANE OF SAID WING STRUCTURE IS GENERALLY NORMAL TO THE LONGITUDINAL AXIS OF SAID FUSELAGE, THRUST MEANS FIXEDLY MOUNTED ON SAID WING STRUCTURE FOR MOVEMENT THEREWITH BETWEEN SAID POSITIONS, SAID THRUST MEANS WHEN ACTIVATED PRODUCING AN AIR FLOW STREAM OVER SAID WING STRUCTURE, YAW CONTROL MEANS ON SAID WING STRUCTURE POSITIONED IN SAID AIR FLOW STREAM FOR DIVIDING SAID AIR FLOW STREAM SELECTIVELY FOR EFFECTING ROTATION OF SAID AIRCRAFT ABOUT ITS VERTICAL AXIS DURING FLIGHT WHEN SAID WING STRUCTURE IS ORIENTED OUT OF SAID FIRST POSITION, SAID YAW CONTROL MEANS COMPRISING PIVOTAL DEFLECTING MEMBERS MOUNTED AT THE OUTBOARD ENDS OF SAID WING STRUCTURE, MEANS MOUNTING SAID DEFLECTING MEMBERS FOR PIVOTAL MOVEMENT INDEPENDENTLY OF SAID THRUST MEANS ON SAID WING STRUCTURE, AND PILOT OPERABLE MECHANISM FOR PIVOTING SAID MEMBERS SELECTIVELY AND DIFFERENTIALLY IN SAID AIR FLOW STREAM.