Power supply system for a propulsion system of an aircraft

15:

• The power supply system as recited in claim 14 wherein the cooling circuit includes a first cooling section associated with the first heat source, the first cooling section passing through the fuel cell unit.

16:

• The power supply system as recited in claim 14 wherein the second heat source includes an electronic control unit.

17:

• The power supply system as recited in claim 16 wherein the electronic control unit is a motor control unit of an electric motor connected to the fuel cell unit for supplying electrical power.

18:

• The power supply system as recited in claim 14 wherein the cooling circuit includes a reservoir for the cooling fluid.

19:

• The power supply system as recited in claim 14 wherein the first optimal operating temperature Topt_1 is greater than the second optimal operating temperature Topt_2 by at least 5 K.

20:

• The power supply system as recited in claim 14 further comprising a controller configured to operate the first heat source at a first temperature T1, and the second heat source at a second temperature T2, with T1 being greater than T2 (T1>T2).

21:

• An aircraft comprising the power supply system as recited in claim 14.

22:

• An airplane comprising the power supply system as recited in claim 14.

24:

• The method as recited in claim 23 wherein the cooling fluid already been utilized for cooling the first heat source is led, at least temporarily and at least in part, through the recirculation circuit and reused for cooling the first heat source before passing through the heat exchanger.

25:

• The method as recited in claim 24 wherein a portion of the cooling fluid recirculated through the recirculation circuit is greater in a first operating state than in a second operating state.

26:

• The method as recited in claim 25 wherein the first operating state corresponds to normal operation.

27:

• A method of employing of a propulsion system of an aircraft, the method comprising utilizing the power supply system as recited in claim 14.