WHEEL DRIVE SYSTEM FOR AN AIRCRAFT COMPRISING A FUEL CELL AS AN ENERGY SOURCE

• US 20110198439A1
• Filed: 07/06/2009
• Published: 08/18/2011
• Est. Priority Date: 07/07/2008
• Status: Active Grant

• Current Assignee: Airbus Operations GmbH (Airbus SE)
• Original Assignee: Airbus Operations GmbH (Airbus SE)
• Inventors: Heinrich, Hans-Jürgen, Kurre, Jens-Dietrich, Rötger, Thomas
• Granted Patent: US 8,668,165 B2
• Time in Patent Office: Days
• US Class Current: 244/50
• CPC Class Codes: B60K 7/0007 the motor being electric
• CPC Class Codes: B60L 58/30 for monitoring or controlling fuel cells
• CPC Class Codes: B60L 58/33 by cooling
• CPC Class Codes: B60L 58/34 by heating
• CPC Class Codes: B64C 25/405 Powered wheels, e.g. for taxing
• CPC Class Codes: B64D 2041/005 Fuel cells
• CPC Class Codes: Y02T 50/80 Energy efficient operational measures, e.g. ground operations or mission management
• CPC Class Codes: Y02T 90/40 Application of hydrogen technology to transportation, e.g. using fuel cells

Abstract

The invention pertains to a wheel drive system for an aircraft that features at least one electric motor and at least one fuel cell as energy source for the electric motor, wherein the electric motor is coupleable to at least one wheel of at least one landing gear of the aircraft. The inventive wheel drive system reduces the fuel consumption and lowers the emission of CO₂ and pollutants—primarily carbon monoxide and unburned hydrocarbons. Persons, vehicles and other aircraft furthermore are not endangered by a jet blast while the aircraft is taxiing because the main engines do not have to be started until the take-off and landing strip is reached. The operation of the inventive wheel drive system furthermore leads to a reduced noise pollution.

Claims

1. A wheel drive system for an aircraft, comprising:

at least one electric motor (8); and

at least one fuel cell (20) as energy source for the electric motor (8); and

control unit (18) for controlling the torque to be generated or absorbed by the electric motor (8);

wherein the electric motor (8) is coupleable to at least one wheel (4, 6) of at least one landing gear (2) of the aircraft;

wherein the electric motor (8) is designed for generating a torque opposite to the rotating direction of the wheel in order to decelerate the aircraft;

wherein the electric motor (8) delivers electric energy to at least one storage unit and/or at least one consumer (24) in the generator mode; and

wherein the storage unit is realized with an electrolysis device.

2. The wheel drive system of claim 1, wherein the storage unit is realized with at least one capacitor and/or at least one battery.

3. The wheel drive system of claim 1 or 2, wherein the electrolysis device is realized with the fuel cell (20).

4. The wheel drive system of one of the preceding claims, furthermore comprising a water storage device for accommodating water from the fuel cell (20).

5. The wheel drive system of one of the preceding claims, wherein the electrolysis device is supplied with water from the water storage device.

6. The wheel drive system of one of the preceding claims, wherein the electric energy supply to other electric consumers (24) of the aircraft is reduced in order to increase the electric energy supply to the electric motor (8).

7. The wheel drive system of one of the preceding claims, wherein the control unit (18) is designed for adjusting a cabin temperature before taxiing in dependence on the outside temperature, namely in such a way that a comfort temperature range is not exceeded during the entire taxiing process despite the throttling of an environmental control system (22).

8. The wheel drive system of one of the preceding claims, wherein the electric motor (8) is coupleable to the wheel (4, 6) by means of a gear drive (10), and wherein a torque sensor (16) arranged in the drive train is connectable to the control unit (18).

9. The use of a wheel drive system, comprising:

at least one electric motor (8);

at least one fuel cell (20) as energy source for the electric motor (8); and

control unit (18) for controlling the torque to be generated or absorbed by the electric motor (8);

wherein the electric motor (8) is coupleable to at least one wheel (4, 6) of at least one landing gear (2) of the aircraft;

wherein the electric motor (8) is designed for generating a torque opposite to the rotating direction of the wheel in order to decelerate the aircraft;

wherein the electric motor (8) delivers electric energy to at least one storage unit and/or at least one consumer (24) in the generator mode; and

wherein the storage unit is realized with an electrolysis device.

10. An aircraft comprising a wheel drive system, comprising:

at least one electric motor (8);

at least one fuel cell (20) as energy source for the electric motor (8); and

control unit (18) for controlling the torque to be generated or absorbed by the electric motor (8);

wherein the electric motor (8) is coupleable to at least one wheel (4, 6) of at least one landing gear (2) of the aircraft;

wherein the electric motor (8) is designed for generating a torque opposite to the rotating direction of the wheel in order to decelerate the aircraft;

wherein the electric motor (8) delivers electric energy to at least one storage unit and/or at least one consumer (24) in the generator mode; and

wherein the storage unit is realized with an electrolysis device.