Convertible vtol aircraft

Claim 1

IN A V/STOL AIRCRAFT, A FUSELAGE, A WING EXTENDING TO EITHER SIDE OF SAID FUSELAGE, AT LEAST TWO ENGINES MOUNTED CENTRALLY OF SAID AIRCRAFT ABOVE SAID WING AND ON OPPOSITE SIDES OF SAID FUSELAGE AND OUTSIDE SAID FUSELAGE, AT LEAST ONE CENTERBODY ON EACH SIDE OF SAID WING, A PROPELLER MOUNTED ON SAID CENTERBODY, A TRANSMISSION SYSTEM FROM SAID ENGINES, ALONG SAID WINGS TO DRIVE SAID PROPELLER, A SLOTTED FLAP MOVABLE BETWEEN RETRACTED POSITION AND PROJECTED POSITION, EACH SAID WING HEAVING A CAVITY TO RECEIVE SAID FLAP IN RETRACTED POSITION, A RIGID, PIVOTAL DEFLECTOR WING, AND MEANS PIVOTALLY MOUNTING SAID DEFLECTOR WING ON THE REARMOST END OF SAID CENTERBODY FOR PIVOTAL MOVEMENT BETWEEN A RETRACTED, SUBSTANTIALLY HORIZONTAL POSITION AND A PROJECTED SUBSTANTIALLY VERTICAL POSITION, SAID FLAP AND DEFLECTOR WING WHEN BOTH IN PROJECTED POSITION FORCING THE SLIPSTREAM OF SAID PROPELLER SUBSTANTIALLY DOWNWARD.