Lift unit for vertical take-off and landing aerial vehicle

• US 7,213,786 B1
• Filed: 10/18/2004
• Issued: 05/08/2007
• Est. Priority Date: 10/18/2004
• Status: Expired due to Fees

• Current Assignee: Charles Cecil Mckinney
• Original Assignee: Charles Cecil Mckinney
• Inventors: McKinney, Charles Cecil
• Primary Examiner(s): Collins; Timothy D.
• Assistant Examiner(s): Lee; Benjamin P.
• Application Number:
  US10/968,330
• Time in Patent Office: 932 Days
• Field of Search: 244/10, 244/21, 244/23.B, 244/23.R
• US Class Current: 244/10
• CPC Class Codes: B64C 23/02 by means of rotating members of cylindrical or similar form
• CPC Class Codes: B64C 29/0008 having its flight directional axis horizontal when grounded

Abstract

A lift unit for a vertical take-off and landing type aerial vehicle. A smooth, cylindrical rotor, rotating at a high rate, as close as is practicable to the smooth, inside of a half-cylindrical, cradle-shaped stator, generates lift. While there is no up or down force within the very small space between the rotor and stator, there is reduced aerodynamic pressure on the exposed upper half of the rotor. Atmospheric pressure remains normal beneath the stator, producing considerable lift. Panels designed to slide over portions of the rotor, vary the lift, either uniformly or differentially to provide control. The streamlined unit is attached in a plurality to the wing of a conventionally configured, fixed-wing aircraft with the axis of the rotor aligned parallel to the thrust line of the vehicle. This lift unit is very efficient and produces no downward efflux, facilitating rescue operations.

Claims

1. A device, having a spinning cylindrical rotor as means for generating an effect of a reduction of atmospheric pressure adjacent to its outside surface and subsequently, by means of contoured partially enclosing surfaces, nullifying said effect of a reduction of atmospheric pressure, selectively, as means for causing an imbalance of atmospheric pressure for providing aerodynamic lift for an aerial vehicle, said device, herein called a lift unit, being made substantially of aluminum, as well as any material being the structural equivalent of aluminum in terms of weight, strength and formability, said lift unit being manufacturable in multiples, as means for a plurality of said lift unit being used as means for symmetrical aerodynamic lift, on said aerial vehicle, comprising:

an elongated circular cylinder of substantial diameter, being hollow and having a polished outside surface, said cylinder having axle segments attached at its extremities, with one said axle segment, having a gear attached as means for receiving rotational energy for said cylindrical rotor;

with said cylinder, said axle segments and said gear, communicating to form said cylindrical rotor;

further comprising;

a stator which is a stationary contoured means for enclosing one half of said cylindrical rotor, from extremity to extremity along its longitudinal axis of rotation, as a means for nullifying said effect of a reduction of atmospheric pressure, within the enclosed area of said stator, said stator having locations at its ends as means for bearings to be fastened for receiving said cylindrical rotor, said stator being positioned at a very small, uniform predetermined gap from said cylindrical rotor, said stator having further means thereon, for mounting said lift unit to the wing of said aerial vehicle;

further comprising;

streamlining means, also fastened to said ends of said stator, said streamlining means for facilitating horizontal flight of said aerial vehicle, after vertical flight is accomplished, said streamlining means having locations thereon, as means for fastening lift variation panels, said lift variation panels, being slidable contoured panels, made able by hydraulic means, for enclosing portions of said cylindrical rotor, selectively, as means to vary aerodynamic lift for accomplishing flight attitude control during the slow aspect of vertical flight of said aerial vehicle;

whereby, as said longitudinal axis of said cylindrical rotor is oriented horizontally with said stator facing downwards as means for having a reduced atmospheric pressure above said lift unit adjacent to the exposed half of said cylindrical rotor facing upwards, with normal atmospheric pressure underneath said lift unit, said lift unit mounted to the wing of said aerial vehicle, with said axis of rotation oriented parallel to the thrust line of said aerial vehicle as means to generate vertical aerodynamic lift when said cylindrical rotor is rotating at a high predetermined rate.