Abstract: A method for humidifying an air supply of a fuel cell, an air supply circuit including an injection line, an intermediate line and an evacuation line. The method includes steps for recovering recycled air, in the evacuation line, and injecting recycled air into the injection line so as to mix it with ambient air from the environment. The method additionally includes increasing the ratio of recycled air in the injection line when a power setting of the cell reduces and if the power setting is lower than a predefined power threshold, and reducing the ratio of recycled air when the power setting increases and if the power setting remains lower than the predefined threshold.

Abstract: A fuel cell power system including at least one fuel cell, a ram air system and a cooling circuit in which coolant is intended to circulate for regulating a temperature of the at least one fuel cell. The cooling circuit comprises a ram air heat exchanger in the ram air system and the ram air system comprises a nozzle. The fuel cell power system further comprises a water tank and the fuel cell power system is arranged to flow water from the water tank to the ram air system so as to spray water in ram air via the nozzle. Thus, dimensioning of the ram air system which includes the ram air heat exchanger is reduced.

Abstract: A system of fuel cells for an aircraft including a plurality of fuel cells, a hydrogen circuit, a cooling circuit and a first air circuit configured to supply oxygen to a first subset of fuel cells having at least two cells. The first air circuit includes an air flow restrictor at each fuel cell inlet of the first subset and configured to distribute the air between the fuel cells of the first subset, and an outlet valve connected to the outlet of the fuel cells of the first subset, the opening of the outlet valve being controlled by a computer as a function of an electrical power that is to be produced by the fuel cells of the first subset. The use of the same air circuit to supply oxygen to several fuel circuits makes it possible to limit the bulk of the fuel cells system.

Abstract: An autonomous propeller propulsion system for an aircraft. The autonomous system comprises a chassis with first attachment systems which engage with second attachment systems of the wing to ensure detachable attachment of the autonomous system, a fuel cell attached to the chassis, an electric motor attached to the chassis and having an output shaft, a propshaft rotated by the output shaft, a propeller attached to the propshaft, a controller converting an electric current delivered by the fuel cells into an electric current delivered to the electric motor, a hydrogen feed duct and an air feed duct, a set of auxiliary equipment, and a first connection arrangement, which connects with a second connection arrangement of the aircraft.

Abstract: A system of fuel cells for an aircraft includes a plurality of fuel cells, a hydrogen circuit, an air circuit, and a first cooling circuit configured to cool a first subset of cells including at least two cells. The first cooling circuit includes a computer-controlled device for mixing a first liquid coolant at a first temperature with a second liquid coolant at a second temperature lower than the first temperature to obtain a liquid coolant having a target temperature, a liquid coolant restrictor configured to distribute the liquid coolant between the cells of the first subset, and an outlet valve, the opening of which is controlled by the computer as a function of the cooling needs of the cells of the first subset. The use of a cooling circuit to cool several fuel circuits makes it possible to limit the bulk of the fuel cells system.

Abstract: A fuel cell power system including at least one fuel cell, a ram air system and a cooling circuit in which coolant is intended to circulate for regulating a temperature of the at least one fuel cell. The cooling circuit comprises a ram air heat exchanger in the ram air system and the ram air system comprises a nozzle. The fuel cell power system further comprises a water tank and the fuel cell power system is arranged to flow water from the water tank to the ram air system so as to spray water in ram air via the nozzle. Thus, dimensioning of the ram air system which includes the ram air heat exchanger is reduced.

Abstract: A system of fuel cells for an aircraft including a plurality of fuel cells, a hydrogen circuit, a cooling circuit and a first air circuit configured to supply oxygen to a first subset of fuel cells having at least two cells. The first air circuit includes an air flow restrictor at each fuel cell inlet of the first subset and configured to distribute the air between the fuel cells of the first subset, and an outlet valve connected to the outlet of the fuel cells of the first subset, the opening of the outlet valve being controlled by a computer as a function of an electrical power that is to be produced by the fuel cells of the first subset. The use of the same air circuit to supply oxygen to several fuel circuits makes it possible to limit the bulk of the fuel cells system.

Abstract: A system of fuel cells for an aircraft includes a plurality of fuel cells, a hydrogen circuit, an air circuit, and a first cooling circuit configured to cool a first subset of cells including at least two cells. The first cooling circuit includes a computer-controlled device for mixing a first liquid coolant at a first temperature with a second liquid coolant at a second temperature lower than the first temperature to obtain a liquid coolant having a target temperature, a liquid coolant restrictor configured to distribute the liquid coolant between the cells of the first subset, and an outlet valve, the opening of which is controlled by the computer as a function of the cooling needs of the cells of the first subset. The use of a cooling circuit to cool several fuel circuits makes it possible to limit the bulk of the fuel cells system.

Abstract: An autonomous propeller propulsion system for an aircraft. The autonomous system comprises a chassis with first attachment systems which engage with second attachment systems of the wing to ensure detachable attachment of the autonomous system, a fuel cell attached to the chassis, an electric motor attached to the chassis and having an output shaft, a propshaft rotated by the output shaft, a propeller attached to the propshaft, a controller converting an electric current delivered by the fuel cells into an electric current delivered to the electric motor, a hydrogen feed duct and an air feed duct, a set of auxiliary equipment, and a first connection arrangement, which connects with a second connection arrangement of the aircraft.

Abstract: A supply system for providing at least oxygen depleted air and water in a vehicle includes a catalytic converter, at least one hydrogen supply means, at least one air supply means, at least one outlet for oxygen depleted air, and a control unit coupled with the catalytic converter. The catalytic converter is couplable with the hydrogen supply means and is adapted for producing water under consumption of hydrogen from the at least one hydrogen supply means and oxygen. The catalytic converter is further couplable with the at least one air supply means for additionally producing oxygen depleted air. Further, the control unit is adapted for selectively operating the catalytic converter based on a demand of water and oxygen depleted air.

Abstract: A fuel cell system for an aircraft includes a fuel cell, wherein at the cathode side a cathode inlet and a cathode outlet is provided, and wherein at the anode side an anode inlet and an anode outlet is provided, and a cathode recirculation channel for passing the cathode product fluid from the cathode outlet to the cathode inlet. In the fuel cell system, the water content of the cathode product fluid in the cathode recirculation channel can be reduced or at least stabilized in a possibly effective way, because the cathode recirculation channel includes a water extraction device for extracting water from the cathode product fluid.

Abstract: A supply system for providing at least oxygen depleted air and water in a vehicle includes a catalytic converter, at least one hydrogen supply means, at least one air supply means, at least one outlet for oxygen depleted air, and a control unit coupled with the catalytic converter. The catalytic converter is couplable with the hydrogen supply means and is adapted for producing water under consumption of hydrogen from the at least one hydrogen supply means and oxygen. The catalytic converter is further couplable with the at least one air supply means for additionally producing oxygen depleted air. Further, the control unit is adapted for selectively operating the catalytic converter based on a demand of water and oxygen depleted air.

Abstract: A supply system for providing at least oxygen depleted air and water in a vehicle includes a catalytic converter, at least one hydrogen supply means, at least one air supply means, at least one outlet for oxygen depleted air, and a control unit coupled with the catalytic converter. The catalytic converter is couplable with the hydrogen supply means and is adapted for producing water under consumption of hydrogen from the at least one hydrogen supply means and oxygen. The catalytic converter is further couplable with the at least one air supply means for additionally producing oxygen depleted air. Further, the control unit is adapted for selectively operating the catalytic converter based on a demand of water and oxygen depleted air.

Abstract: A fuel cell system for an aircraft includes a fuel cell, wherein at the cathode side a cathode inlet and a cathode outlet is provided, and wherein at the anode side an anode inlet and an anode outlet is provided, and a cathode recirculation channel for passing the cathode product fluid from the cathode outlet to the cathode inlet. In the fuel cell system, the water content of the cathode product fluid in the cathode recirculation channel can be reduced or at least stabilized in a possibly effective way, because the cathode recirculation channel includes a water extraction device for extracting water from the cathode product fluid.

Abstract: A fuel cell system for an aircraft includes a fuel cell, wherein at the cathode side a cathode inlet and a cathode outlet is provided, and wherein at the anode side an anode inlet and an anode outlet is provided, and a cathode recirculation channel for passing the cathode product fluid from the cathode outlet to the cathode inlet. In the fuel cell system, the water content of the cathode product fluid in the cathode recirculation channel can be reduced or at least stabilized in a possibly effective way, because the cathode recirculation channel includes a water extraction device for extracting water from the cathode product fluid.

Abstract: A system for cooling an aircraft fuel cell system comprising a first cooling circuit thermally coupled to a first fuel cell, to remove thermal energy generated by the first fuel cell during operation from the first fuel cell, and a first heat exchanger arranged in the first cooling circuit and adapted to transfer thermal energy, removed from the first fuel cell via the first cooling circuit, to the aircraft surroundings. The system comprises a second cooling circuit thermally coupled to a second fuel cell, to remove thermal energy generated by the second fuel cell during operation from the second fuel cell, and a second heat exchanger arranged in the second cooling circuit and adapted to transfer thermal energy, removed from the second fuel cell via the second cooling circuit, to the aircraft surroundings. The first cooling circuit is thermally couplable to the second cooling circuit.

Abstract: A fuel cell system for an aircraft includes a fuel cell, wherein at the cathode side a cathode inlet and a cathode outlet is provided, and wherein at the anode side an anode inlet and an anode outlet is provided, and a cathode recirculation channel for passing the cathode product fluid from the cathode outlet to the cathode inlet. In the fuel cell system, the water content of the cathode product fluid in the cathode recirculation channel can be reduced or at least stabilized in a possibly effective way, because the cathode recirculation channel includes a water extraction device for extracting water from the cathode product fluid.

Abstract: A supply system for providing at least oxygen depleted air and water in a vehicle includes a catalytic converter, at least one hydrogen supply means, at least one air supply means, at least one outlet for oxygen depleted air, and a control unit coupled with the catalytic converter. The catalytic converter is couplable with the hydrogen supply means and is adapted for producing water under consumption of hydrogen from the at least one hydrogen supply means and oxygen. The catalytic converter is further couplable with the at least one air supply means for additionally producing oxygen depleted air. Further, the control unit is adapted for selectively operating the catalytic converter based on a demand of water and oxygen depleted air.

Abstract: A fuel cell system for a vehicle comprises at least one fuel cell, at least one fuel cell heat exchanger arranged in or at the at least one fuel cell for receiving heat of the at least one fuel cell, at least one thermal dissipation unit, at least one additional heat exchanger and a cooling loop having a plurality of fluid line segments for conveying a coolant. The at least one fuel cell heat exchanger is coupled with the at least one thermal dissipation unit through the cooling loop, and the additional heat exchanger is arranged in the cooling loop and is adapted for receiving heat from an external source and for raising the temperature of a coolant flowing in the cooling loop.

Abstract: A system for cooling an aircraft fuel cell system comprising a first cooling circuit thermally coupled to a first fuel cell, to remove thermal energy generated by the first fuel cell during operation from the first fuel cell, and a first heat exchanger arranged in the first cooling circuit and adapted to transfer thermal energy, removed from the first fuel cell via the first cooling circuit, to the aircraft surroundings. The system comprises a second cooling circuit thermally coupled to a second fuel cell, to remove thermal energy generated by the second fuel cell during operation from the second fuel cell, and a second heat exchanger arranged in the second cooling circuit and adapted to transfer thermal energy, removed from the second fuel cell via the second cooling circuit, to the aircraft surroundings. The first cooling circuit is thermally couplable to the second cooling circuit.