POWER SUPPLY SYSTEM FOR A PROPULSION SYSTEM OF AN AIRCRAFT

A power supply system () for a propulsion system () of an aircraft (), including a first heat source () in the form of a fuel cell unit (), a second heat source (), and a heat exchanger (). The first and second heat sources () and the heat exchanger () are connected to one another in a cooling circuit () for conducting a cooling fluid (). The first heat source () has a first optimal operating temperature Tand the second heat source () has a second optimal operating temperature T. The first optimal operating temperature Tis greater than the second optimal operating temperature T(T>T). A recirculation circuit () is associated with the first heat source () in the cooling circuit (), via which cooling fluid () already utilized during operation for cooling the first heat source () is reusable for cooling the first heat source () before passing through the heat exchanger (). The heat exchanger () includes an actuatable inlet ().