Vertical lift aircraft

Claim 1

A VERTICAL LIFT AIRCRAFT COMPRISING AN ANNULAR FUSELAGE SYMMETRICAL ABOUT A SUBSTANTIALLY VERTICAL AXIS OF REVOLUTION AND HAVING INTERCONNECTED UPPER AND LOWER WALLS, THE UPPER WALL INCLUDING AN ANNULAR AIRFOIL PORTION CIRCUMSCRIBING SAID AXIS AND HAVING CHORDS SUBSTANTIALLY RADIAL TO THE AXIS, A SHAFT ROTATABLY MOUNTED COAXIALLY IN THE FUSELAGE, AN ENGINE MOUNTED IN THE FUSELAGE AND CONNECTED IN DRIVING RELATION TO THE SHAFT FOR IMPARTING ROTATION THERETO, A PROPELLER SECURED TO THE SHAFT ABOVE THE UPPER WALL OF THE FUSELAGE AND POSITIONED WITHIN THE AIRFOIL PORTION FOR DRAWING AIR AXIALLY INWARDLY THEREOF AND DISCHARGING SAID AIR OUTWARDLY THEREOF, MEANS MOUNTED ON THE UPPER WALL OF THE FUSELAGE LOCATED BETWEEN THE PROPELLER AND THE AIRFOIL PORTION FOR GUIDING AIR DISCHARGED BY THE PROPELLER IN A RADIAL DIRECTION FROM SAID AXIS AND LOCATED ABOVE THE AIRFOIL TO FORM AN ANNULAR AIR PASSAGE WITH AIRFOIL, AND INFLATABLE AZIMUTHAL CONTROL MEMBERS MOUNTED IN THE AIRFOIL PORTION AT PREDETERMINED PERIPHERAL LOCATIONS THEREAROUND FOR SELECTED DISTENSION INTO SAID AIR PASSAGE AND CONTRACTION THEREFROM TO CONTROL THE FLOW OF AIR OUTWARDLY OVER THE AIRFOIL PORTION WHEREBY THE RESULTANT LIFT MAY BE REGULATED AND HORIZONTAL MOVEMENT IMPARTED TO THE AIRCRAFT.