A power generation system for an aircraft includes: a storage tank for storing hydrogen; a fuel cell configured to generate power from the hydrogen; a fuel supply line configured to supply the hydrogen from storage tank to the fuel cell; a fresh air supply line configured to supply air to a cabin air supply system; and a fuel-air heat exchange system, wherein the fuel supply line and the air supply line pass through the fuel-air heat exchange system such that the hydrogen cools the air in use.

An air processing system for an aircraft comprising a hydrogen fuel cell. The air processing system includes an input airflow; a first and a second compressor, wherein each compressor is configured to compress the airflow in a compression stage; a first and a second turbine, wherein each turbine is configured to decompress the airflow in a decompression stage; and a first and a second shaft each configured to independently rotate. Each shaft mechanically couples one of the compressors and one of the turbines, such that torque can be transferred between the compressor-turbine pair.

An air processing system for an aircraft comprising a hydrogen fuel cell. The air processing system includes an input airflow; a first and a second compressor, wherein each compressor is configured to compress the airflow in a compression stage; a first and a second turbine, wherein each turbine is configured to decompress the airflow in a decompression stage; and a first and a second shaft each configured to independently rotate. Each shaft mechanically couples one of the compressors and one of the turbines, such that torque can be transferred between the compressor-turbine pair.

A flying vehicle with a fuselage having a longitudinal axis, a cockpit extending substantially from the center of the fuselage, a left front wing extending from the fuselage, a right front wing extending from the fuselage, a left rear wing extending from the fuselage, a right rear wing extending from the fuselage. Each wing contains a rotor rotatably mounted and a direct drive brushless motor providing directional control of the vehicle. A centrally located ducted fan encompasses the cockpit and provides VTOL capabilities. The central location of the cockpit and central ducted fan aid in balance and stability. The central ducted fan is itself a brushless motor with the stator windings encapsulated in the ducted fan housing and rotor magnets within the fan. All motors and rotatable mounts are controlled by a fly-by-wire system integrated into a central computer with avionics allowing for autonomous flight.

An aircraft propulsion system includes an energy conversion device that uses a cryogenic fuel and air to generate power and thermal energy, and a bottoming cycle where a working fluid is circulated within a closed circuit that includes a bottoming compressor section and a bottoming turbine section. A primary heat exchanger provides thermal communication of thermal energy from the energy conversion device to the working fluid of the bottoming cycle. A second heat exchanger is in thermal communication with the working fluid and a heat source other than from the energy conversion device for changing a temperature of the working fluid flow.

An aircraft propulsion system includes an energy conversion device that uses a cryogenic fuel and air to generate power and thermal energy, and a bottoming cycle where a working fluid is circulated within a closed circuit that includes a bottoming compressor section and a bottoming turbine section. A primary heat exchanger provides thermal communication of thermal energy from the energy conversion device to the working fluid of the bottoming cycle. A second heat exchanger is in thermal communication with the working fluid and a heat source other than from the energy conversion device for changing a temperature of the working fluid flow.

A propulsion system including an electric motor, the output of which drives a propeller, and a reversible fuel cell comprising a cathode and an anode connected to the electric motor, a supply line connecting the fuel cell to the dihydrogen tank and a feed line connecting the fuel cell to the temporary water tank.

A propulsion system including an electric motor, the output of which drives a propeller, and a reversible fuel cell comprising a cathode and an anode connected to the electric motor, a supply line connecting the fuel cell to the dihydrogen tank and a feed line connecting the fuel cell to the temporary water tank.

The present disclosure provides systems and methods for propulsion. The system may comprise one or more motor assemblies for driving at least one shaft or rotor of a vehicle. The motor assemblies may comprise one or more motor windings and/or magnets. The system may comprise one or more fuel cells in fluid communication with the motor assemblies. The fuel cells may be configured to generate electrical energy from a fuel that is directed through a portion of the motor assemblies to (i) cool the motor windings and the magnets and (ii) and heat the fuel before the fuel enters the fuel cells. The system may comprise a combustion chamber in fluid communication with the fuel cells. The combustion chamber may be configured to combust an exhaust flow from the fuel cells to (i) react unused hydrogen exhausted from the fuel cells and (ii) provide thermal and/or mechanical power.

The present disclosure provides systems and methods for propulsion. The system may comprise one or more motor assemblies for driving at least one shaft or rotor of a vehicle. The motor assemblies may comprise one or more motor windings and/or magnets. The system may comprise one or more fuel cells in fluid communication with the motor assemblies. The fuel cells may be configured to generate electrical energy from a fuel that is directed through a portion of the motor assemblies to (i) cool the motor windings and the magnets and (ii) and heat the fuel before the fuel enters the fuel cells. The system may comprise a combustion chamber in fluid communication with the fuel cells. The combustion chamber may be configured to combust an exhaust flow from the fuel cells to (i) react unused hydrogen exhausted from the fuel cells and (ii) provide thermal and/or mechanical power.