A propulsion system for an aircraft includes an electric generator and a turbomachine. The turbomachine is configured to be mounted to a first wing of the aircraft and is operable with the electric generator. The propulsion system additionally includes a first propulsor mechanically coupled to a shaft of the turbomachine and a second propulsor assembly configured to be mounted at a location away from the turbomachine and the first propulsor. The electric generator is in electrical communication with the second propulsor assembly for powering the second propulsor assembly.

An electric propulsion and lift system for an aircraft that includes a plurality of electric motor/propeller assemblies on the flaps of the aircraft so that when the flaps are deflected for take-off and landings, the propellers are directed downward to provide thrust for power lift and increased airflow over the wing for aerodynamic lift. The motor/propeller assemblies are spaced apart and positioned along the entire length of the flaps to provide a distributed airflow.

The Distributed Electric Ducted Fan Wing concept incorporates multiple electric ducted fans on lifting surfaces configured to provide integrated aerodynamics and propulsion resulting in enhanced aerodynamic characteristics and thus aircraft performance. The concept uses a plurality of electric ducted fans (EDFs) to not only provide thrust, but to also blow air across the upper surface of a substantial portion of the lifting surface area increasing lift at little loss in efficiency. Not only can the total lift on the surfaces be enhanced, but the lift distribution managed: to aid in aircraft control; ameliorate the effects of turbulence: reduce shed vortices; mitigate the effects of system failures; eliminate stalls; and compensate for crosswinds. This concept offers the potential for increasing electric airplane efficiency and performance, enhancing Short Takeoff and Landing (STOL) capabilities, improving passenger comfort, and reducing the structural stress and cost of aircraft.

An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements and a set of tail mounted rotors for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle uses different configurations of its wing mounted rotors and propellers to reduce drag in all flight modes.

An aircraft cooling system comprises an evaporator, condenser, an accumulator, and a pump system. The evaporator is configured to cool a set of heat loads in an aircraft using a liquid. The liquid forms a vapor in response to cooling the set of heat loads. The condenser is configured to receive the vapor from the evaporator and cool the vapor in which cooling the vapor forms the liquid. The accumulator is configured to receive the liquid from the condenser and store the liquid. The pump system is configured to pump the liquid stored in the accumulator to the evaporator.

An aircraft comprises a fuselage, wings connected to the fuselage, engines connected to the wings, and liquid hydrogen tanks. Each engine in the engines comprises a nacelle, an electric motor within the nacelle, a fuel cell stack within the nacelle, and a nacelle heat exchanger within the nacelle that receives air flowing through an inlet in the nacelle. The liquid hydrogen tanks are configured to store liquid hydrogen, wherein the liquid hydrogen tanks extend along an outside of the fuselage and above the wings and below windows in the fuselage.

An aircraft comprises a fuselage, wings connected to the fuselage, engines connected to the wings, and liquid hydrogen tanks. Each engine in the engines comprises a nacelle, an electric motor within the nacelle, a fuel cell stack within the nacelle, and a nacelle heat exchanger within the nacelle that receives air flowing through an inlet in the nacelle. The liquid hydrogen tanks are configured to store liquid hydrogen, wherein the liquid hydrogen tanks extend along an outside of the fuselage and above the wings and below windows in the fuselage.

A heat exchanger system for an aircraft comprises nacelle having an inlet and an outlet, a nacelle heat exchanger within the nacelle, and a fan system within the nacelle. Air flows into the nacelle through the inlet and out of the nacelle through the outlet. The nacelle heat exchanger is configured to transfer heat away from a coolant using the air in an airflow to the nacelle heat exchanger. The fan system is configured to increase the airflow to the nacelle heat exchanger.

An integrated hydrogen FC electric engine includes a centrifugal compressor and a turbine rotatably mounted, back-to-back on a common shaft; and one or more FCs arranged around an outside of the rotatably mounted centrifugal compressor and the rotatably mounted turbine. The integrated hydrogen FC electric engine is compact enough to fit into the nacelle of an aircraft.

An integrated hydrogen FC electric engine includes a centrifugal compressor and a turbine rotatably mounted, back-to-back on a common shaft; and one or more FCs arranged around an outside of the rotatably mounted centrifugal compressor and the rotatably mounted turbine. The integrated hydrogen FC electric engine is compact enough to fit into the nacelle of an aircraft.