초록 ▼

A powered nose aircraft wheel system (130) for an aircraft (12) includes landing gear (104) that extends from the aircraft (12). A wheel axel (136) is coupled to the landing gear (104). A wheel (134) is coupled to the wheel axel (136). A wheel motor (106) is coupled to the wheel axel (136) and the w

A powered nose aircraft wheel system (130) for an aircraft (12) includes landing gear (104) that extends from the aircraft (12). A wheel axel (136) is coupled to the landing gear (104). A wheel (134) is coupled to the wheel axel (136). A wheel motor (106) is coupled to the wheel axel (136) and the wheel (134). A controller (120) is coupled to the wheel motor (106) and rotates the wheel (134). A method of taxiing an aircraft (12) includes permitting the wheel (134) of the aircraft (12) to freely spin during the landing of the aircraft (12). Power is transferred from an auxiliary power unit (73) of the aircraft (12) to the wheel motor (106). The wheel (134) is rotated via the wheel motor (106). The aircraft (12) is steered and the speed of the wheel (134) is controlled via one or more controllers selected from an onboard controller (18, 118, 120) and an offboard controller (45, 58, 59).

대표청구항 ▼

What is claimed is: 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

What is claimed is: 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.