Patent ID: 8668165
Filing Date: 2014-03-11
Classification: B60K,B60L,B64C,B64D,Y02T

Abstract:
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.