Patent ID: 11878805
Assignee: U.S. AERONAUTICS, INC.
Field: Transport (Mechanical engineering)
Classification: CPC B  F  Y | IPC B  F

Claim 0:
1. A propulsion system for an aircraft, the propulsion system comprising:
a reciprocating engine housed within a fuselage;
a continuously variable transmission housed within the fuselage and configured to be mounted at least partially above the reciprocating engine;
a liquid cooled exhaust system internal to the fuselage;
a first ducted-fan assembly, external to the fuselage, powered by the reciprocating engine via a drive shaft connected to the continuously variable transmission internal to the fuselage;
a turbocharger, internal to the fuselage, configured to compress engine inlet air to control a temperature and a pressure of the air entering the reciprocating engine; and
a liquid cooled exhaust manifold, internal to the fuselage, configured to cool exhaust air prior to the exhaust air entering a catalytic converter;
wherein the first ducted-fan assembly comprises rotatable fan blades having an adjustable pitch;
wherein the first ducted-fan assembly comprises stators that receive an airflow off the rotatable fan blades;
wherein the drive shaft enters a duct of the first ducted-fan assembly through a stator of the stators.