Disclosed are a power supply device for air mobility and a method thereof. The power supply device includes a plurality of power supply lines that distribute power of a fuel cell stack in parallel, one-to-one matches the plurality of power supply lines with a plurality of rotor structures. The power supply device supplies power to one rotor structure through one power supply line, thereby supplying power to the remaining rotor structures through the remaining power supply lines even when a short circuit occurs in a semiconductor switching element on any one of the plurality of power supply lines.

Disclosed are a power supply device for air mobility and a method thereof. The power supply device includes a plurality of power supply lines that distribute power of a fuel cell stack in parallel, one-to-one matches the plurality of power supply lines with a plurality of rotor structures. The power supply device supplies power to one rotor structure through one power supply line, thereby supplying power to the remaining rotor structures through the remaining power supply lines even when a short circuit occurs in a semiconductor switching element on any one of the plurality of power supply lines.

The invention is directed to an air supply device and to a method for supplying at least one fuel cell of an aircraft fuel cell drive with compressed air, wherein the aircraft fuel cell drive has an air supply device comprising a compressor arrangement, wherein ambient air is compressed by means of the compressor arrangement and a first part of the compressed air is supplied to the at least one fuel cell and a second part of the compressed air can be diverted to a cooling device of the at least one fuel cell by means of a bypass device.

A method for cooling an electrical aircraft propulsion system includes decreasing a temperature of a portion of a coolant below an operating temperature, acting this portion of the coolant as a thermal buffer, and maintaining a rest of the coolant at the operating temperature.

A method for cooling an electrical aircraft propulsion system includes decreasing a temperature of a portion of a coolant below an operating temperature, acting this portion of the coolant as a thermal buffer, and maintaining a rest of the coolant at the operating temperature.

This patent discloses a powerplant for an aerial vehicle comprised of Perovskite-Silicon tandem photovoltaic solar cells covering the wings and fuselage, a lithium-sulfur battery, a high-pressure unitized regenerative proton exchange membrane (PEM) device, and hydrogen tanks. The PEM device has a fuel-cell mode and an electrolysis mode. During level flight, the PEM device operates in fuel-cell mode, converting hydrogen into electricity. The electricity is used to run a plurality of pairs of permanent magnet synchronous motors, coupled to propellers, and mounted in a coaxial rotor configuration. During level flight, the array of solar cells re-charges the LiS battery pack. During takeoff and landing, the LiS battery pack supplements the electricity generated by the PEM device in fuel-cell mode. On the ground, the solar cells provides electricity to the PEM device, which operates in electrolysis mode, converting water into hydrogen gas, which is then stored in the hydrogen tanks.

This patent discloses a powerplant for an aerial vehicle comprised of Perovskite-Silicon tandem photovoltaic solar cells covering the wings and fuselage, a lithium-sulfur battery, a high-pressure unitized regenerative proton exchange membrane (PEM) device, and hydrogen tanks. The PEM device has a fuel-cell mode and an electrolysis mode. During level flight, the PEM device operates in fuel-cell mode, converting hydrogen into electricity. The electricity is used to run a plurality of pairs of permanent magnet synchronous motors, coupled to propellers, and mounted in a coaxial rotor configuration. During level flight, the array of solar cells re-charges the LiS battery pack. During takeoff and landing, the LiS battery pack supplements the electricity generated by the PEM device in fuel-cell mode. On the ground, the solar cells provides electricity to the PEM device, which operates in electrolysis mode, converting water into hydrogen gas, which is then stored in the hydrogen tanks.

A system and method for having a fuel cell wastewater balancer. The wastewater balancer includes a hydrogen tank which stores hydrogen to be consumed by a fuel cell and a ballast tank which stores wastewater produced as a biproduct of the fuel cell reaction. A controller maintains the center of gravity of an aircraft by distributing wastewater to the ballast tank as hydrogen is consumed by the fuel cell.

A system and method for having a fuel cell wastewater balancer. The wastewater balancer includes a hydrogen tank which stores hydrogen to be consumed by a fuel cell and a ballast tank which stores wastewater produced as a biproduct of the fuel cell reaction. A controller maintains the center of gravity of an aircraft by distributing wastewater to the ballast tank as hydrogen is consumed by the 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.