A power source
assembly (200, 300, 400) for an aeronautical vehicle (100), includes a fuel
cell module (202, 302, 312, 402, 412) configured to provide a first
direct current (DC)
power output, a battery module (204, 304, 314, 404, 414) configured to provide a second DC
power output, a DC
electric bus (206, 306, 316, 406, 416) configured to provide a specified DC
power output to a load (212, 324, 422), a multi-phase DC /
DC converter including a plurality of converter units (214), the multi-phase DC /
DC converter configured to receive the first DC power output from the fuel
cell module (202, 302, 312, 402, 412) and the second DC power output from the battery module (204, 304, 314, 404, 414) and to provide the specified DC power output to the DC
electric bus (206, 306, 316, 406, 416), and a controller (210, 310, 320, 410, 420, 600) operably coupled to the multi-phase DC /
DC converter and configured to receive data (602D) indicative of the first DC power output, the controller (210, 310, 320, 410, 420, 600) configured to control the plurality of converter units (214) of the multi-phase DC / DC converter based on the data (602D) indicative of the first DC power output to maintain the specified DC power output to the load (212, 324, 422).