Tilt wing aircraft

Claim 1

A TILT WING AIRCRAFT COMPRISING A FUSELAGE, WING STRUCTURE PIVOTALLY MOUNTED ON SAID FUSELAGE AND SELECTIVELY MOVABLE BETWEEN A HORIZONTAL POSITION AND A VERTICAL POSITION, SAID CRAFT WHEN SAID WING STRUCTURE IS IN SAID VERTICAL POSITION BEING ADAPATED FOR VERTICAL TAKE-OFF AND LANDING, THRUST MEANS ON SAID WING STRUCTURE FOR PROPELLING SAID AIRCRAFT IN ALL POSITIONS OF SAID WING STRUCTURE, MEANS FOR SELECTIVELY PIVOTALLY SAID WING STRUCTURE BETWEEN SAID POSITION WHILE SAID AIRCRAFT IS IN FLIGHT, AT LEAST ONE LIFT MEMBER ON SAID WING STRUCTURE FOR DIRECTING A FORCE AGAINST SAID WING STRUCTURE GENERALLY TRANSVERSELY THEREOF WHEN ACTUATED, SEPARATE PILOT OPERABLE YAW AND ROLLS CONTROLS OPERATIVELY CONNECTED WITH SAID THRUST MEANS AND SAID LIFT MEMBER FOR SELECTIVELY ACTUATING AND REGULATING SAID THRUST MEANS AND SAID LIFT MEMBER DURING FLIGHT, AND INTERGRATING MECHANISM INTERPOSED BETWEEN SAID PILOT CONTROLS AND SAID THRUST MEAND AND SAID LIFT MEMBER FOR INTEGRATING AND CORRELATING OPERATION OF SAID THRUST MEANS AND SAID LIFT MEMBER, SAID MECHANSIM BEING CONDITIONED WHEN SAID WING STRUCTURE IS IN ANY INTERMEDIATE POSITION OF TRANSITION BETWEEN SAID HORIZONTAL AND SAID VERTICAL POSITIONS TO GRADIENTLY MODIFY THE EFFECT OF MOVEMENT OF EACH OF SAID YAW AND ROLL PILOT CONTROLS ON SAID THRUST MEANS AND ON SAID LIFT MEMBER AS SAID WING STRUCTURE IS PIVOTED BETWEEN SAID HORIZONTAL AND SAID VERTICAL POSITIONS.