Aircraft propulsion system with intermittent combustion engine(s)

An aircraft system, comprising:

• a first propulsor rotor rotatable about a first propulsor axis;
• a first vane array downstream of the first propulsor rotor;
• a first transmission coupled to the first propulsor rotor;
• a second propulsor rotor rotatable about a second propulsor axis;
• a second vane array downstream of the second propulsor rotor;
• a second transmission coupled to the second propulsor rotor;
• and
• a turbo-compounded intermittent combustion engine configured to drive rotation of the first propulsor rotor through the first transmission, and the turbo-compounded intermittent combustion engine configured to drive rotation of the second propulsor rotor through the second transmission.

An aircraft system, comprising:

• an aircraft fuselage;
• a first propulsor outside of the aircraft fuselage;
• a second propulsor outside of the aircraft fuselage;
• and
• an intermittent combustion engine housed within the aircraft fuselage, wherein the first propulsor and the second propulsor are discretely powered by the intermittent combustion engine such that during
• a first mode of operation, the first propulsor and the second propulsor are operable to provide matching thrust;
• and
• a second mode of operation, the first propulsor is operable to provide first thrust and the second propulsor is operable to provide second thrust that is different than the first thrust.