Drive system for an aircraft

17:

• The drive system as recited in claim 16 wherein the interconnector is configured to transfer the second electrical power of the second power generator proportionally to the first propulsion unit if the fault condition of the first drive unit is a fault of the first power generator.

18:

• The drive system as recited in claim 16 wherein the interconnector is configured to transfer the first electrical power of the first power generator at least proportionally to the second propulsion unit if the fault condition of the first drive unit is a fault of the first propulsion unit.

19:

• The drive system as recited in claim 16 wherein the interconnector is configured to interconnect the second propulsion unit or the second power generator with the first drive unit to supply power in the event of a fault condition of the second drive unit.

21:

• The drive system as recited in claim 16 wherein the first or the second power generator are each fuel cell systems.

22:

• The drive system as recited in claim 21 wherein the fuel cell systems have at least two fuel cell stacks.

23:

• The drive system as recited in claim 16 wherein the first and second propulsion units each have an electric motor and a shaft having a propeller.

24:

• The drive system as recited in claim 23 wherein the electric motor, the shaft and the propeller are oversized with respect to the power generator.

25:

• An aircraft comprising:
• the drive system as recited in claim 16, wherein a power of the first and second drive units during a failure is greater than the first or second electrical power respectively in a respectively comparable normal operation without a failure of the first or second drive unit.

26:

• The aircraft as recited in claim 25 wherein the aircraft is an airplane having a first and a second win, wherein the first drive unit is arranged on the first wing and the second drive unit is arranged on the second wing, thus supply is distributed from one side of the aircraft to the other using the interconnector in the event of a fault condition.

27:

• The aircraft as recited in claim 25 wherein the aircraft is an airplane having a first and a second wing, wherein the first drive unit and the second drive are arranged on the first wing.

28:

• A method for operating the drive system as recited in claim 16, the method comprising interconnecting the first propulsion unit or the first power generator with the second drive unit to supply power in the event of a fault condition of the first drive unit.

29:

• The method as recited in claim 28 wherein the second electrical power of the second power generator is transferred proportionally to the first propulsion unit if the fault condition of the first drive unit is a fault of the first power generator.

30:

• The method as recited in claim 28 wherein the first electrical power of the first power generator is at least proportionally transferred to the second propulsion unit if the fault condition of the first drive unit is a fault of the first propulsion unit.