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A counter rotating ducted fan having a permanent magnet drive. comprising a ducted housing having an iron core stator and a pair of counter rotating propeller blades rotationally mounted on a propeller shaft positioned axially within the housing Each of the propeller blades includes a plurality of

A counter rotating ducted fan having a permanent magnet drive. comprising a ducted housing having an iron core stator and a pair of counter rotating propeller blades rotationally mounted on a propeller shaft positioned axially within the housing Each of the propeller blades includes a plurality of individual propeller blades of an even number. Permanent magnets are mounted in permanent magnet insertion holes located at the tip of each of the individual propeller blades. When excited by an electrical current a pair of excitation windings mounted within the iron core stator control the rotational speed and direction of the pair of counter rotating propeller blades.

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What is claimed is: 1. An aerial vehicle for air transportation comprising: (a) a vehicle body; (b) a cylindrical shaped ducted housing centrally located within said vehicle body, said cylindrical shaped ducted housing including: (i) first and second stators, said first stator being positioned in a

What is claimed is: 1. An aerial vehicle for air transportation comprising: (a) a vehicle body; (b) a cylindrical shaped ducted housing centrally located within said vehicle body, said cylindrical shaped ducted housing including: (i) first and second stators, said first stator being positioned in an upper portion of said ducted housing, and said second stator being positioned in a lower portion of said ducted housing; (ii) said first and second stators having a stator core and a plurality of excitation windings; (iii) said stator core for said first and second stators having a core portion and a stator salient pole portion, said core portion forming a magnetic circuit to generate a magnetic flux and then pass said magnetic flux to the stator salient pole portion of said stator core; and (iv) said first and second stators having said plurality of excitation windings wound round said stator salient pole portion for said first and second stators in a uniform and concentrated manner; (c) first and second counter rotating propellers rotatably mounted within said cylindrical shaped ducted housing, said first counter rotating propellers being positioned within the upper portion of said cylindrical shaped ducted housing, and said second counter rotating propellers being positioned within the lower portion of said cylindrical shaped ducted housing, said first and second counter rotating propellers being operative to provide vertical takeoff and landing and translational flight capabilities for said aerial vehicle; (d) said first and second counter rotating propellers having a plurality of equally spaced apart blades, each of said plurality of blades having a permanent magnet located at a tip of said blade; and (e) an electromagnetic drive controller connected to the plurality of excitation windings of said first and second counter rotating propellers, said electromagnetic drive controller providing electrical current to the excitation windings of said first and second counter rotating propellers to generate said magnetic flux, said magnetic flux passing through the permanent magnets for said first and second counter rotating propellers generating torque which when applied to the blades for each of said counter rotating propellers causes the blades for each of said counter rotating propellers to rotate. 2. The aerial vehicle of claim 1 wherein said plurality of blades for said first and second counter rotating propellers comprises eight equally spaced apart blades. 3. The aerial vehicle of claim 1 wherein said plurality of blades for said first and second counter rotating propellers an even number of said blades in a range of six equally spaced apart blades to sixteen equally spaced apart blades. 4. The aerial vehicle of claim 1 wherein said electromagnetic drive controller controls a magnitude and direction of current flow through the excitation windings of said first and second counter rotating propeller blades which allows for adjustments to and control of a rotational speed and a direction of rotation of each of said first and second counter rotating propeller blades. 5. The aerial vehicle of claim 1 wherein said excitation windings of said first and second counter rotating propellers are copper wire excitation windings. 6. The aerial vehicle of claim 1 wherein said first and second stators are fabricated from a metal selected from the group consisting of iron, aluminum alloys and silicon steel, said metal having electromagnetic properties which allow each of said first and second stators to generate a magnetic field of sufficient strength to rotate said first and counter rotating propellers. 7. The aerial vehicle of claim 1 wherein said permanent magnet for each of said plurality of blades is mounted within a permanent magnet insertion holes located at the tip of each blade. 8. The aerial vehicle of claim 1 wherein said permanent magnets are arranged alternatively as north, south, north, south poles within each of said first and second counter rotating propellers forming a ring structure at the periphery of each of said first and second counter rotating propellers. 9. The aerial vehicle of claim 1 further comprising a shaft mounted vertically within the interior of said ducted housing, said first and second counter rotating propeller blades being rotatably mounted on said shaft. 10. The aerial vehicle of claim 1 further comprising a plurality of direction control vane assemblies mounted within said cylindrical shaped ducted housing at a bottom end of said cylindrical shaped ducted housing, said plurality of direction control vane assemblies controlling directional movement of said aerial vehicle in a flight mode of operation, said plurality of direction control vane assemblies including: (a) first, second, third and fourth direction control vane assemblies configured to form a rectangle within said duct housing; (b) fifth and sixth aligned direction control vane assemblies positioned diagonally within said rectangle; and (c) seventh and eighth aligned direction control vane assemblies positioned diagonally within said rectangle, said seventh and eighth direction control vane assemblies being perpendicular to said fifth and sixth direction control vane assemblies. 11. An aerial vehicle for air and ground transportation comprising: (a) a vehicle body; (b) a cylindrical shaped ducted housing centrally located within said vehicle body, said cylindrical shaped ducted housing including: (i) first and second stators, said first stator being positioned in an upper portion of said ducted housing, and said second stator being positioned in a lower portion of said ducted housing; (ii) said first and second stators having a stator core and a plurality of excitation windings; (iii) said stator core for said first and second stators having a core portion and a stator salient pole portion, said core portion forming a magnetic circuit to generate a magnetic flux and then pass said magnetic flux to the stator salient pole portion of said stator core; and (iv) said first and second stators having said plurality of excitation windings wound round said stator salient pole portion for said first and second stators in a uniform and concentrated manner; (c) first and second counter rotating propellers rotatably mounted within said cylindrical shaped ducted housing, said first counter rotating propellers being positioned within the upper portion of said cylindrical shaped ducted housing, and said second counter rotating propellers being positioned within the lower portion of said cylindrical shaped ducted housing, said first and second counter rotating propellers being operative to provide vertical takeoff and landing and translational flight capabilities for said aerial vehicle; (d) said first and second counter rotating propellers having a plurality of equally spaced apart blades, each of said plurality of blades having a permanent magnet located at a tip of said blade; and (e) an electromagnetic drive controller connected to the plurality of excitation windings of said first and second counter rotating propellers, said electromagnetic drive controller providing electrical current to the excitation windings of said first and second counter rotating propellers to generate said magnetic flux, said magnetic flux passing through the permanent magnets for said first and second counter rotating propellers generating torque which when applied to the blades for each of said counter rotating propellers causes the blades for each of said counter rotating propellers to rotate; (f) a plurality of direction control vane assemblies mounted within said cylindrical shaped ducted housing at a bottom end of said cylindrical shaped ducted housing, said plurality of direction control vane assemblies controlling directional movement of said aerial vehicle in a flight mode of operation; (g) a first wheel and axle assembly positioned at the rear end of said aerial vehicle, said first wheel and axle assembly including first and second drive wheels, the first drive wheel being rotatably mounted on one side of said of aerial vehicle and the second drive wheel being rotatably mounted on an opposite side of said aerial vehicle; (h) a gasoline engine and transmission assembly operatively connected to said first wheel and axle assembly to provide power to said first and second drive wheels rotating said first and second drive wheels when said aerial vehicle is in a ground based mode of operation; (i) a second wheel and axle assembly positioned at a front end of said aerial vehicle, said second wheel and axle assembly including first and second steerable wheels, the first steerable wheel being rotatably mounted on the one side of said aerial vehicle and the second steerable wheel being rotatably mounted on the opposite side of said aerial vehicle; and (j) a steering wheel mounted within a cockpit located in proximity to the front end of said aerial vehicle, said steering wheel being operatively connected to said second wheel and axle assembly to allow a user of said aerial vehicle to steer said first and second steerable wheels and maneuver said aerial vehicle on a roadway when said aerial vehicle is in said ground based mode of operation. 12. The aerial vehicle of claim 11 wherein said plurality of blades for said first and second counter rotating propellers comprises eight equally spaced apart blades. 13. The aerial vehicle of claim 11 wherein said plurality of blades for said first and second counter rotating propellers an even number of said blades in a range of six equally spaced apart blades to sixteen equally spaced apart blades. 14. The aerial vehicle of claim 11 wherein said electromagnetic drive controller controls a magnitude and direction of current flow through the excitation windings of said first and second counter rotating propeller blades which allows for adjustments to and control of a rotational speed and a direction of rotation of each of said first and second counter rotating propeller blades. 15. The aerial vehicle of claim 11 wherein said excitation windings of said first and second counter rotating propellers are copper wire excitation windings. 16. The aerial vehicle of claim 11 wherein said first and second stators are fabricated from a metal selected from the group consisting of iron, aluminum alloys and silicon steel, said metal having electromagnetic properties which allow each of said first and second stators to generate a magnetic field of sufficient strength to rotate said first and counter rotating propellers. 17. The aerial vehicle of claim 11 wherein said permanent magnet for each of said plurality of blades is mounted within a permanent magnet insertion holes located at the tip of each blade. 18. The aerial vehicle of claim 11 wherein said permanent magnets are arranged alternatively as north, south, north, south poles within each of said first and second counter rotating propellers forming a ring structure at the periphery of each of said first and second counter rotating propellers. 19. The aerial vehicle of claim 11 further comprising a shaft mounted vertically within the interior of said ducted housing, said first and second counter rotating propeller blades being rotatably mounted on said shaft. 20. The serial vehicle of claim 11 wherein said plurality of direction control vane assemblies comprise: (a) first, second, third and fourth direction control vane assemblies configured to form a rectangle within said duct housing; (b) fifth and sixth aligned direction control vane assemblies positioned diagonally within said rectangle; and (c) seventh and eighth aligned direction control vane assemblies positioned diagonally within said rectangle, said seventh and eighth direction control vane assemblies being perpendicular to said fifth and sixth direction control vane assemblies.