Powered nose aircraft wheel system

1. A powered nose aircraft wheel system for an aircraft comprising:

aircraft nose landing gear extending from the aircraft;

at least one wheel axel coupled to said landing gear;

at least one wheel coupled to said at least one wheel axel;

at least one electric wheel motor coupled to said at least one wheel axel and said at least one wheel, wherein said at least one wheel motor comprises a rotor and a stator, and performs as at least one of a motor, a generator, and a brake;

a drive assembly coupled to said at least one wheel motor and said at least one wheel and transferring energy therebetween wherein said drive assembly comprises a dual activated engagement mechanism for forward and reverse operation which is adapted to permit a wheel to freely spin during a high speed condition and to be used as a source of rotational energy for regenerative energy return and to be pre-spun prior to landing of the aircraft to minimize wear and system shock upon touchdown;

an auxiliary power unit or a ground based power supply and delivery system, said at least one wheel motor coupled to and receiving power from said auxiliary power unit or ground based supply; and

a controller coupled to said at least one wheel motor and rotating said at least one wheel.

2. A system as in claim 1 wherein said controller directs the aircraft to and from a terminal gate via said at least one wheel motor.

3. A system as in claim 1 further comprising a receiver coupled to said controller, said controller receiving remotely generated control signals and maneuvers the aircraft in response to said control signals.

4. A system as in claim 1 further comprising a guidance control system generating control signals, said controller maneuvers the aircraft in response to said control signals.

5. A system as in claim 1 wherein said controller depowers aircraft main engines prior to or during engagement of said at least one wheel motor.

6. A system as in claim 1 wherein said controller maneuvers the aircraft in response to pilot command signals.

7. A system as in claim 1 wherein said drive assembly comprises a gear, said controller rotating said gear in a first direction to move the aircraft forward and in a second direction to move the aircraft rearward.

8. A system as in claim 1 wherein said drive assembly disengages from said at least one wheel when said wheel rotates at a speed approximately equal to or greater than rotation speed of said drive assembly.

9. A system as in claim 1 wherein said dual activated engagement mechanism comprises:

at least one gear; and

a clutch assembly coupled to said at least one gear;

said at least one gear and said clutch assembly engaging said at least one wheel with said at least one wheel motor.

10. A system as in claim 9 wherein said clutch assembly is a dual activated cone mechanism.

11. A system as in claim 1 wherein said controller pre-spins said at least one wheel prior to landing of the aircraft.

12. A system as in claim 1 further comprising an aircraft terminal mating system thereby providing a ground support system.

13. A ground support system as in claim 12 wherein said aircraft terminal mating system is in the form of a machine vision technology system.

14. A ground support system as in claim 12 wherein said aircraft terminal mating system comprises a docking coupler.

15. A ground support system as in claim 12 wherein said aircraft terminal mating system comprises a global positioning system.

16. A ground support system as in claim 12 wherein said aircraft terminal mating system comprises a precision guidance system that follows a guideline in mating the at least one aircraft to at least one airport interface terminal docking port.

17. An integrated operational ground mobility system comprising:

a remotely located offboard controller transmitting control signals; and

at least one aircraft comprising a powered nose aircraft wheel system comprising:

aircraft nose landing gear extending from said at least one aircraft;

at least one wheel axel coupled to said landing gear;

at least one wheel coupled to said wheel axel;

at least one electric wheel motor coupled to said wheel axel and said at least one wheel; wherein said at least one wheel motor comprises a rotor and a stator, and performs as at least one of a motor, a generator, and a brake;

a drive assembly coupled to said at least one wheel motor and said at least one wheel and transferring energy therebetween wherein said drive assembly comprises a dual activated engagement mechanism for forward and reverse operation which is adapted to permit a wheel to freely spin during a high speed condition, and to be used as a source of rotational energy for regenerative energy return, and to be pre-spun prior to landing of the aircraft to minimize wear and system shock upon touchdown;

an auxiliary power unit or a ground based power supply and delivery system, said at least one wheel motor coupled to and receiving power from said auxiliary power unit or ground based supply; and

an onboard controller coupled to said at least one wheel motor and rotating said at least one wheel in response to said control signals.

18. A system as in claim 17 further comprising a global positioning system coupled and providing guidance information to said onboard controller.