Abstract: A lighter-than-air craft includes an envelope defining an interior region. A lifting gas at least partially including hydrogen is located within the interior region. The lifting gas provides buoyancy for the lighter-than-air craft. A hydrogen fuel cell is fluidically coupled with the interior region. An inerting gas is located within the envelope, and the inerting gas at least partially includes exhaust from the hydrogen fuel cell. The inerting gas and the lifting gas have respective volumes such that a mixture thereof is nonflammable during operating conditions for the lighter-than-air craft. The hydrogen fuel cell is able to utilize the hydrogen of the lifting gas to generate electricity. A propulsion system is coupled to the envelope and is able to provide propulsion for the lighter-than-air craft.

Abstract: Disclosed is a system for controlling gaseous hydrogen (GH2) refueling of a GH2 vehicle, wherein a vehicle fuel tank is refilled with GH2 from an external supply tank. The system includes a target patch or a cell of a temperature-dependent reflectivity material on an exterior of the vehicle fuel tank, and a sensor package including an electromagnetic (EM) radiation emitter and a radiation detection system positioned remote from the vehicle tank being filled. The sensor package is located on or adjacent an external refueling device with a line of sight to the target patch or cell.

Abstract: A hydrogen boiloff capture system. The hydrogen boiloff capture system having a cryogenic tank for storing liquid hydrogen. The hydrogen boiloff capture system also includes an intermediate tank fluidically coupled with the cryogenic tank. The intermediate tank is configured to receive hydrogen gas boiloff from the cryogenic tank. The intermediate tank is further configured to provide the hydrogen gas boiloff to a lighter-than-air craft to regulate buoyancy of the lighter-than-air craft. The intermediate tank is also configured to provide the hydrogen gas boiloff to a hydrogen fuel cell coupled to the lighter-than-air craft.

Abstract: A cooling architecture for an integrated hydrogen-electric engine having a radiator and a hydrogen fuel cell includes a t and a manifold. The turbine is disposed in fluid communication with the hydrogen fuel cell. The turbine is configured to compress a predetermined amount of air and direct a first portion of the predetermined amount of the compressed air to the fuel cell for generating electricity that powers the integrated hydrogen-electric engine. The manifold is disposed in fluid communication with the turbine and positioned to direct a second portion of the predetermined amount of compressed air to the radiator for removing heat from the radiator.

Abstract: A fuel cell system having at least one fuel cell having an external surface; and one or more of audio, image, or strain sensors external to the fuel cell surface, configured for detecting a change in the external surface of the fuel cell indicative of a fault condition. The at last one sensor may include a visual camera, an IR camera, an IR detector, or a UV-responsive camera, or an ultrasound transducer, a piezoelectric sensor and a vibration sensor, or a surface acoustic wave detector, or a mass spectrometer.

Abstract: The disclosure relates to bipolar plates used in fuel cells and to methods for forming bipolar plates. A bipolar plate of a fuel cell with a composite corrosion-resistant, gastight, conductive coating comprises a core of a required shape, a first layer having high contact conductivity on the core, and a second layer having corrosion resistance, high gas-tightness, electric conductivity on the first layer and in pores of the first layer, the second layer covering at least the pores in the first layer. The first layer is preferably formed by a magnetron sputtering method, and the second layer is preferably formed by a method of thermolysis of a metalorganic compound. This ensures high gas-tightness and elasticity of a bipolar plate without compromising its corrosion resistance and contact conductivity.

Abstract: A lighter-than-air craft including an envelope. A mixture of helium and hydrogen disposed within the envelope. The mixture having a ratio of helium to hydrogen such that the mixture is nonflammable during operating conditions for the lighter-than-air craft. The mixture provides buoyancy for the lighter-than-air craft. A hydrogen fuel cell fluidically coupled with the mixture and configured to utilize the mixture to generate electricity. A propulsion system is coupled to the envelope, and the propulsion system is configured to provide propulsion for the lighter-than-air craft. The propulsion system is electrically coupled with the hydrogen fuel cell and receives electricity generated by the hydrogen fuel cell. The propulsion system is configured to utilize the electricity in providing the propulsion to the lighter-than-air craft.

Abstract: The method allows to produce catalysts with nanoparticles of platinum and its alloys with metals of a given composition, with high values of catalytic activity in an oxygen electroreduction reaction, and with predetermined values of structural characteristics. The method comprises preparation of a solution of chloroplatinic acid or a mixture of chloroplatinic acid with metal salts, mixing thereof with dispersed carbon or non-carbon carriers, their mixtures and compositions with specific surface area of more than 60 m2/g, dispersion of the obtained mixture, chemical reduction of compounds of platinum and a metal salt with subsequent deposition of nanoparticles of metallic platinum or its alloys on a dispersed carrier being carried out by purging gases selected from: nitrogen oxides (N2O, NO, NO2), carbon oxides (CO, CO2), sulfur oxide (SO2), ammonia (NH3) or their mixtures through the solution at a temperature of the solution in the range from 5 to 98° C.

Abstract: A fuel-cell-powered vehicle includes an electrically-powered turbine assembly having a housing, a rotating shaft, an air compressor comprising a compressor stator fixed to the housing and a compressor rotor fixed to the rotating shaft, an electric motor including an electric motor stator fixed to the compressor stator and an electric motor rotor fixed to the rotating shaft, a turbine including a turbine stator affixed to the housing, a turbine rotor fixed to the rotating shaft, and two or more fuel cells arranged around an outside of the electrically-powered turbine assembly.

Abstract: The present disclosure relates to fuel cells, in particular to high-temperature air-cooled fuel cells. A fuel cell 1 comprises a bipolar plate 2 and a membrane-electrode assembly 3. The bipolar plate 2 comprises an anode plate 5, a cathode plate 6 and a layer 7 of air cooling channels between the anode plate 5 and the cathode plate 6. Channels for an oxygen-containing gas are made in the cathode plate 6. Channels 10 for hydrogen are made in the anode plate 5, which are covered by the membrane-electrode assembly 3 contacting the anode plate 5. A fuel cell stack comprises at least two fuel cells, wherein the membrane-electrode assembly of one fuel cell contacts the anode plate of said one fuel cell, thus covering the channels for hydrogen, and contacts the cathode plate of said another fuel cell, which adjoins said one fuel cell, thus covering the channels for an oxygen-containing gas.

Abstract: A cryogenic fuel tank for retrofitting a conventional fossil-fuel-powered aircraft, or for a purposely built aircraft to run on hydrogen has an aerodynamically shaped outer surface including an ogive shaped nose cone, and a tapered tail cone, wherein the tapered tail cone includes actively adjustable elements for adjusting aerodynamic characteristics of the cryogenic fuel tank. The cryogenic fuel tank is configured to be attached below wings of the aircraft, through support pylons, which include sensors configured to measure forces applied by the cryogenic fuel tank to the airframe. The cryogenic fuel tank includes a nozzle and valve configured to vent gas from the cryogenic fuel tank by expansion through the nozzle in the event that the cryogenic fuel tank is jettisoned from the aircraft.

Abstract: Disclosed is a system for humidifying cabin and/or cockpit air of a fuel cell-powered aircraft system. The system includes a fuel cell stack configured for reacting hydrogen and oxygen to produce electrical energy and a cathode exhaust containing moist, warm air; a water separator configured to cool the moist, warm air and to condense and separate liquid water from the moist, warm air; and a humidifier configured to employ the separated liquid water to humidify pressurized cabin air.

Abstract: In one or more embodiments of the novel aircraft fuel cell system without the use of a buffer battery, the fuel cell and compressor would be sized sufficiently larger for the intended application, allowing the compressor to change speeds much faster. This in turn would allow power outputs to change much quicker. If power outputs can change as quickly as the application dictates, then a buffer battery is not necessary. In one or more embodiments, because the system is mostly electronically controlled, software can be written to protect the fuel cell from instantaneous power spikes. If a large power output is suddenly requested of the fuel cell, the software can smooth out the demand curve to provide an easier load profile to follow.

Abstract: A liquid hydrogen (LH2) fuel storage system for a fuel cell-powered vehicle, and method includes a main LH2 storage fuel tank configured for close to ambient pressure storage of LH2, and one or more gas accumulator tanks (GATs) smaller than the main LH2 storage fuel tank and configured for elevated pressure storage of LH2 and for feeding pressurized LH2 to the fuel cell, wherein the one or more GATs each have a cooling interface configured to cool the GAT employing LH2 from the main LH2 storage fuel tank, and a heating interface configured to heat contents of the GAT with warm working fluid from the fuel cell-powered vehicle whereby to raise pressure of the LH2 in the GAT to a working pressure for feeding the LH2 to the fuel cell.

Abstract: An integrated hydrogen-electric includes a hydrogen fuel cell; a hydrogen fuel source; an electric motor assembly disposed in electrical communication with the fuel cell; n air compressor system configured to be driven by the motor assembly, and a cooling system having a heat exchanger radiator in a duct of the cooling system, and configured to direct an air stream including an air stream from the air compressor through the radiator, wherein an exhaust stream from a cathode side of the fuel cell is fed via an flow control nozzle into the air stream in the cooling duct downstream of the radiator.

Abstract: A power generating system comprised of a hydrogen fuel cell and rechargeable battery connected together in series to be used as a load following system without the use of a DC-DC converter. The hydrogen fuel cell's cathode air compressor is driven off of the output of this power generation system. This is made possible by the following innovations: A novel way to wire the systems in series with the use of switches and bypass diodes, a method to limit the system output voltage so that we do not exceed the maximum voltage of downstream components, and an isolated DC-DC converter to charge the rechargeable battery with the hydrogen fuel cell.

Abstract: Method and system for managing hydrogen fuel in hydrogen fuel cell-powered aircraft is disclosed. The method identifies unused hydrogen fuel in a fuel tank of the aircraft. Determines an amount of the unused hydrogen fuel in the fuel tank of the aircraft. Transfers the amount of the unused hydrogen fuel from the fuel tank of the aircraft into a hydrogen fuel cell of the aircraft and converts the amount of the unused hydrogen fuel into electricity via the hydrogen fuel cell of the aircraft.

Abstract: An integrated fuel cell power delivery system includes a first power source configured to supply power to a propulsion inverter, a second power source configured to supply power to the propulsion inverter, a disconnect operably connected to the second power source, a bypass diode operably connected to the first power source and the second power source, a sensor that detects an output voltage of the integrated fuel cell power system, a processor, and a memory. The memory includes instructions stored thereon, which when executed by the processor, cause the integrated fuel cell power system to access a signal from the sensor, determine if the accessed first signal is greater than a first threshold voltage, and operably disconnect an output of the second power source to the integrated fuel cell power system by the disconnect based on the determination.

Abstract: A system and method for an aircraft evacuation system with hydrogen inflation is disclosed. The system includes an aircraft having an integrated hydrogen-electric engine. A fuel cell stack for powering an aircraft motor of the integrated hydrogen-electric engine. A hydrogen fuel source in fluid communication with the fuel cell stack, the hydrogen fuel source containing hydrogen. An inflatable slide and a pump operably coupled with the hydrogen fuel source and the inflatable slide to selectively pump the hydrogen to the inflatable slide for inflating the inflatable slide.

Abstract: An air compression system for a fuel cell system, the air compression system has a main air compressor with a maximum air flow output approximately equal to a continuous mode air flow requirement of the fuel cell system. The main air compressor weighs less than an air compressor having a maximum air flow output approximately equal to a peak air flow requirement of the fuel cell system such that the weight of the air compression system is reduced compared to a conventional air compression system. The air compression system also includes a supplemental oxygen supply system which is fluidically coupled with the fuel cell system.