A cooling system for a fuel cell onboard a vehicle includes a coolant circuit and a thermal energy storage device in fluid communication with the coolant circuit. The coolant circuit defines a coolant passageway and is configured to circulate a coolant through the coolant passageway and through a portion of the fuel cell to absorb heat from the fuel cell. The thermal energy storage device includes a phase change material configured to store thermal energy released from the coolant flowing through the coolant circuit and through the thermal energy storage device in the form of latent heat. The phase change material is configured to dissipate thermal energy stored therein to a circumambient airflow flowing relative to the vehicle when the vehicle is moving.

A cooling system for a fuel cell onboard a vehicle includes a coolant circuit and a thermal energy storage device in fluid communication with the coolant circuit. The coolant circuit defines a coolant passageway and is configured to circulate a coolant through the coolant passageway and through a portion of the fuel cell to absorb heat from the fuel cell. The thermal energy storage device includes a phase change material configured to store thermal energy released from the coolant flowing through the coolant circuit and through the thermal energy storage device in the form of latent heat. The phase change material is configured to dissipate thermal energy stored therein to a circumambient airflow flowing relative to the vehicle when the vehicle is moving.

A propulsion assembly for an aircraft, having a T-shaped chassis with a horizontal structure and a vertical structure, a gearbox fastened to a front of the chassis, and a propulsion system having the following propulsion elements: an electric motor driving the components of the gearbox, a fuel cell, a tank and a cooling system, wherein the propulsion elements are fastened beneath the horizontal structure and against the vertical structure by fastening means.

A propulsion assembly for an aircraft, having a T-shaped chassis with a horizontal structure and a vertical structure, a gearbox fastened to a front of the chassis, and a propulsion system having the following propulsion elements: an electric motor driving the components of the gearbox, a fuel cell, a tank and a cooling system, wherein the propulsion elements are fastened beneath the horizontal structure and against the vertical structure by fastening means.

A sustainable water fueled process and apparatus where a Unipolar electrolysis of water is described and the hydrogen and oxygen are stored before feeding a hydrogen fuel cell which is capable of providing sufficient electricity to provide power to a drive a vehicle, power a generator etc, after supplying electricity to the Unipolar electrolyser and the storage of the hydrogen and oxygen.

A refueling system for hydrogen fuel cell-powered aircraft is disclosed. The system includes a compressor to receive a source of low temperature, high pressure hydrogen gas and compress the low temperature, high pressure hydrogen gas into a higher temperature, higher pressure hydrogen gas. A compression chamber within the compressor to receive the higher temperature, higher pressure hydrogen gas from the compressor. A valve coupled with the compression chamber to reduce the pressure of the higher temperature, higher pressure hydrogen gas to a higher temperature, lower pressure hydrogen gas. A storage container on an aircraft to receive the higher temperature, lower pressure hydrogen gas via the pressure relief valve. A heat exchanger in thermal cooperation with the compression chamber, the heat exchanger configured to absorb heat from the compression chamber and convert the heat into storable energy.

An airship comprises a main body having a rigid structure surrounding a plurality of containers for a lighter-than-air gas, a plurality of propeller units mechanically connected to the rigid structure and each comprising one or more electric motors for driving a thrust propeller, and one or more power-generating units for powering the electric motors. The airship also comprises two nacelles symmetrically arranged on either side of the main body and each configured to receive one or more of the power-generating units, each ducted nacelle comprising a mechanical structure connected to the rigid structure of the main body by joint, a fail safe interface, and at least one rod or stay cable between a first point of attachment on the rigid structure of the main body and a second point of attachment on the mechanical structure of the nacelle.

A propulsion system for an aircraft as disclosed herein may include a nacelle, a shaft positioned centrally within a cylindrical passageway of the nacelle, a fan coupled to one end of the shaft, a turbine coupled to an opposite end of the shaft, an electric motor coupled to the shaft, a compressor positioned within the cylindrical passageway, and a solid oxide fuel cell positioned with a hollow ring-shaped interior of the nacelle. The hollow ring-shaped interior may surround and be isolated from the cylindrical passageway. The turbine may be configured to provide primary torque to the shaft while the electric motor may be configured to provide additional torque to the shaft. The electric motor may be powered an electric output of the solid oxide fuel cell while the turbine may be powered at least in part by output gases from the solid oxide fuel cell.

A propulsion system for an aircraft as disclosed herein may include a nacelle, a shaft positioned centrally within a cylindrical passageway of the nacelle, a fan coupled to one end of the shaft, a turbine coupled to an opposite end of the shaft, an electric motor coupled to the shaft, a compressor positioned within the cylindrical passageway, and a solid oxide fuel cell positioned with a hollow ring-shaped interior of the nacelle. The hollow ring-shaped interior may surround and be isolated from the cylindrical passageway. The turbine may be configured to provide primary torque to the shaft while the electric motor may be configured to provide additional torque to the shaft. The electric motor may be powered an electric output of the solid oxide fuel cell while the turbine may be powered at least in part by output gases from the solid oxide fuel cell.

Examples provide an electric propulsion system; the system comprising a nacelle comprising an aerodynamic annular housing defining an internal annular volume and defining an inner duct, only a single one fan stage comprising a fan bearing a plurality of aerodynamic surfaces/blades to generate thrust, and a powertrain comprising at least one electric motor to drive the fan and at least one electrical power source to power the electric motor; and wherein the fan is disposed within the inner duct and the powertrain is disposed within the internal annular volume.