Wheel drive system for aircraft with a fuel cell as energy source
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 wheel drive system reduces the fuel consumption and lowers the emission of CO 2 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 wheel drive system furthermore leads to a reduced noise pollution.
1. An aircraft, comprising:
at least one electric motor; and
at least one fuel cell as energy source for the at least one electric motor;
a control unit for controlling the torque to be generated or absorbed by the at least one electric motor; and
at least one landing gear;
wherein the at least one electric motor is coupled to at least one wheel of the at least one landing gear;
wherein the at least one electric motor is configured for generating a torque opposite to the rotating direction of the at least one wheel to decelerate the aircraft;
wherein the at least one electric motor is configured to deliver electric energy to at least one storage unit or at least one electric consumer in a generator mode;
wherein the at least one electric motor and the at least one fuel cell are configured to be the exclusive power source to the at least one landing gear to enable taxiing and other ground operations of the aircraft; and
wherein the at least one storage unit comprises a water electrolysis device wherein the control unit is programmed for adjusting a temperature in a cabin of the aircraft before taxiing relative to the outside temperature in such a way that a comfort temperature range is not exceeded during the entire taxiing process due to a temporary loss of power to the environmental control system during the taxiing of the aircraft.
2. The aircraft of claim 1 , wherein the electrolysis device comprises the fuel cell.
3. The aircraft of claim 1 , further comprising a water storage device for accommodating water from the fuel cell.
4. The aircraft of claim 3 , wherein the electrolysis device is supplied with water from the water storage device.
5. The aircraft of claim 1 , wherein the control unit is programmed to initiate a reduction of electric energy supply to the at least one electric consumer of the aircraft in order to increase the electric energy supply to the at least one electric motor.
6. The aircraft of claim 1 , wherein the at least one electric motor is coupled to the at least one wheel by a gear drive, and wherein a torque sensor arranged in a drive train is connected to the control unit.