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1. An aircraft propulsion system, comprising: at least one hydraulic pump; at least one intermittent internal combustion (IC) engine configured to drive the at least one hydraulic pump; at least one hydraulic motor in communication with the at least one hydraulic pump and configured to drive at least one propulsor fan; at least one engine oil pump; and a cooling system that includes fluid-air heat exchanger (AIR-EO HEX) configured to transfer thermal energy between a flow of an engine oil and a flow of ambient air, and a first fluid-to-fluid heat exchanger (EO-HF HEX) configured to transfer thermal energy between the flow of the engine oil and a flow of a hydraulic fluid; wherein the at least one hydraulic pump is sized to power the at least one hydraulic motor with the hydraulic oil, and to provide sufficient motive force to the hydraulic oil to cause the hydraulic oil to pass through the at least one hydraulic motor and the EO-HF HEX and back to the at least one hydraulic pump; wherein the at least one engine oil pump is sized to provide sufficient motive force to the engine oil to pass the engine oil to and through the AIR-EO HEX, and thereafter to and through the EO-HF HEX, and thereafter to and through the intermittent IC engine; a second fluid-to-fluid heat exchanger (EO-EC HEX) configured to transfer thermal energy between the flow of the engine oil and a flow of an engine coolant; and at least one engine coolant pump; wherein the at least one engine coolant pump is configured to provide motive force to pass the engine coolant to and through the EO-EC HEX, and to and through the intermittent IC engine; and wherein the motive force provided to the engine oil produced by the at least one engine oil pump is sufficient to pass the engine oil to and through the EO-EC HEX, and thereafter to pass the engine oil to and through the intermittent IC engine.
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