An assembly for an aircraft having a propeller, including an engine assembly having an engine shaft configured for driving engagement with the propeller. The engine assembly includes first and second heat exchangers configured for circulation of at least one of a liquid coolant and a lubricant therethrough. A wheel well is configured for receiving a retracted landing gear. A first cooling duct receives the first heat exchanger and has a first outlet downstream of the first heat exchanger, and a second cooling duct receives the second heat exchanger and has a second outlet downstream of the second heat exchanger. The outlets are in direct fluid communication with an environment of the aircraft, and laterally spaced from each other. The wheel well is located between the outlets. A method of cooling an engine assembly is also discussed.

An assembly for an aircraft having a propeller, including an engine assembly having an engine shaft configured for driving engagement with the propeller. The engine assembly includes first and second heat exchangers configured for circulation of at least one of a liquid coolant and a lubricant therethrough. A wheel well is configured for receiving a retracted landing gear. A first cooling duct receives the first heat exchanger and has a first outlet downstream of the first heat exchanger, and a second cooling duct receives the second heat exchanger and has a second outlet downstream of the second heat exchanger. The outlets are in direct fluid communication with an environment of the aircraft, and laterally spaced from each other. The wheel well is located between the outlets. A method of cooling an engine assembly is also discussed.

An aircraft includes a fuselage; a wing coupled to, and extending from, the fuselage; and a propulsion system. The propulsion system includes a plurality of electric fans integrated into the wing and oriented to generate thrust along a vertical direction, the plurality of electric fans arranged along a length of the wing and including an outer-most electric fan along a transverse direction relative to the fuselage. The outer-most electric fan is at least one of a variable pitch fan or a variable speed fan to provide increased stability to the aircraft.

A method is provided for operating a propulsion system of a vertical takeoff and landing aircraft, the propulsion system including a turbomachine, an electric machine, a forward thrust propulsor, and a plurality of vertical thrust electric fans. The method includes driving the forward thrust propulsor with the turbomachine; rotating the electric machine with the turbomachine to generate electrical power; determining a failure condition of the turbomachine; and providing electrical power to the electric machine to drive the forward thrust propulsor with the electric machine in response to determining the failure condition of the turbomachine.

An aircraft of a modular type including: at least one rotor suitable for providing in full or in part propulsion and/or lift for the aircraft; at least one power plant of the combustion engine type or of the electric motor type; a main gearbox, for mechanically transmitting drive torque generated by the at least one power plant to the at least one rotor; and an avionics system for assisting in piloting the aircraft. In accordance with the invention, the avionics system is configured for automatically providing the assistance in piloting the aircraft when the aircraft has a first power plant only or when the aircraft has a first power plant and a second power plant.

An aircraft of a modular type including: at least one rotor suitable for providing in full or in part propulsion and/or lift for the aircraft; at least one power plant of the combustion engine type or of the electric motor type; a main gearbox, for mechanically transmitting drive torque generated by the at least one power plant to the at least one rotor; and an avionics system for assisting in piloting the aircraft. In accordance with the invention, the avionics system is configured for automatically providing the assistance in piloting the aircraft when the aircraft has a first power plant only or when the aircraft has a first power plant and a second power plant.

An aircraft system is provided that includes a first propulsor, a second propulsor, a drivetrain and an intermittent combustion engine. The first propulsor includes a first propulsor rotor and a first vane array. The second propulsor includes a second propulsor rotor and a second vane array. The drivetrain includes a drive structure and a transmission. An output of the transmission is coupled to the first propulsor rotor and the second propulsor rotor through the drive structure. The intermittent combustion engine is configured to drive rotation of the first propulsor rotor and the second propulsor rotor through the drivetrain.

An aircraft propulsion system comprising a reciprocating liquid cooled engine housed within the fuselage driving twin fuselage mounted ducted-fans is disclosed. The propulsion system may be liquid cooled with a liquid cooled exhaust and at least one turbocharger. The ducted-fans may run fan blade tip speeds of up to 97% Mach driven by a near constant RPM engine through a continuously variable transmission. The propulsion system may be low noise and may meet environmental standards typical in the automotive industry.

An aircraft propulsion system comprising a reciprocating liquid cooled engine housed within the fuselage driving twin fuselage mounted ducted-fans is disclosed. The propulsion system may be liquid cooled with a liquid cooled exhaust and at least one turbocharger. The ducted-fans may run fan blade tip speeds of up to 97% Mach driven by a near constant RPM engine through a continuously variable transmission. The propulsion system may be low noise and may meet environmental standards typical in the automotive industry.

In an air mobility vehicle, an engine operates as required to provide mechanical driving force or electric energy. A battery is charged with the electric energy from the engine. Main rotors operate using the electric energy of the battery and electric power generated by the engine to perform takeoff, landing, and cruising. Auxiliary rotors are disposed at or adjacent to the center of gravity of a vehicle body and mechanically connected to the engine via a clutch. The auxiliary rotors perform the takeoff, the landing, or the cruising by receiving the mechanical driving force from the engine when the clutch is in an engaged position. A controller monitors the states of the battery and the main rotors and controls the operations of the engine and the clutch.