Propulsion system for an aircraft

An aircraft extending between a forward end and an aft end comprising:

• a fuselage;
• an empennage at the aft end of the aircraft;
• a wing assembly extending from the fuselage;
• and
• a propulsion system comprising
• an electric power source comprising a combustion motor and a generator, the combustion motor attached to at least one of the fuselage, the empennage, or the wing assembly;
• an electric propulsor assembly attached to at least one of the fuselage, the empennage, or the wing assembly and configured to generate thrust for the aircraft;
• and
• a power bus electrically connecting the electric power source to the electric propulsor assembly such that the electric power source powers the electric propulsor assembly, the power bus comprising an electric line and a fluid cooling system, wherein the fluid cooling system extends along a length of the electric line and in thermal communication with the electric line for cooling the electric line during operation.

A propulsion system for an aircraft, the propulsion system comprising:

• an electric power source;
• an electric propulsor assembly configured to generate thrust for the aircraft;
• and
• a power bus electrically connecting the electric power source to the electric propulsor assembly such that the electric power source powers the electric propulsor assembly, the power bus comprising a first electric line and a second electric line, the power bus further comprising a fluid cooling system having a first fluid cooling conduit defining a coolant flow direction towards the electric propulsor assembly and a second fluid cooling conduit defining a coolant flow direction towards the electric power source, at least a portion of the first electric line extending in thermal communication with the first fluid cooling conduit and at least a portion of the second electric line extending in thermal communication with the second fluid cooling conduit.