Patent ID: 6581872
Filing Date: 2003-06-24
Classification: B64C

Abstract:
A circular Vertical Take-Off and Landing (VTOL) aircraft comprising:an aerodynamic disc shaped airframe; a central jet turbo-prop engine mounted in a vertical axis position and geared to turn contra-rotating co-axial propellers which provide thrust for the aircraft and hovering flight; at least one turbojet engine mounted horizontally and secured to a central turntable unit which can be steered through 360 degrees to enable the aircraft to move horizontally in any direction; a funnel-shaped annular chamber within the airframe wherein the contra-rotating propellers draw air downward into an annular intake in the top surface of the aircraft, said propellers forcing air downward and outward to an annular exit vent in the underside of the aircraft; a central flight-deck having a hemispherical canopy at the top of the aircraft, said flight-deck being supported above the at least one turbo-jet engine by a structural frame; a plurality of aerodynamic control vanes situated in the lower area of the annular chamber and hinged to operate in the airflow from the propellers in order to affect the pitch, roll and yaw of the aircraft; a plurality of aerodynamic vanes within the annular chamber in the airflow from the propellers in order to generate additional lift force; a plurality of thrust deflecting flaps that can be lowered from the underside of the aircraft to deflect the horizontal jet thrust and to act as airbrakes.