Abstract: A fire fighting system for extinguishing a fire, which has a fuel cell for producing a nitrogen-enriched cathode exhaust air. The fuel cell is supplied with air and a fuel. Within the fuel cell, the air is then reduced to a determined oxygen content. The exhaust air is supplied to the fire source.

Abstract: A fuel cell system for an aircraft is stated, which fuel cell system comprises a fuel cell unit and a suction module. The suction module is used to draw oxygen through the fuel cell unit. No vacuum generators are used during cruising flight.

Abstract: An aircraft fuel cell system includes a fuel cell which has an oxidant inlet for supplying an oxygen-containing medium to the fuel cell. An oxidant supply line has a first end which is connected to the oxidant inlet of the fuel cell. A second end of the oxidant supply line is connectable to a used air outlet of a cabin of the aircraft. A heat exchanger is located in the oxidant supply line and thermally couples the oxygen-containing medium flowing through the oxidant supply line and a second medium flowing through an air conditioning process air line of an air conditioning unit, the heat exchanger being located downstream of a cabin air compressor in the air conditioning process air line.

Abstract: The invention relates to a mixing system for inerting a gas volume. A first exhaust gas that is provided by a fuel cell, and a second exhaust gas that is provided by a hydrogen reformer, can be mixed to form an inert gas mixture. The mixture can be fed into the gas volume for inerting.

Abstract: A fire protection system for reducing the danger of fire, which has a fuel cell for producing a nitrogen-enriched cathode exhaust air. The fuel cell is supplied with air and a fuel. Within the fuel cell, the air is then reduced to a determined oxygen content. The exhaust air is supplied to the room to be protected.

Abstract: A power regulator and a process regulator, or a power regulating device for regulating hybrid energy sources are provided for an aircraft. The power regulator and process regulator is equipped such that the requirement of a required means of a consumer is measurable. In this arrangement the power regulating device is equipped such that a first operating characteristic of a first energy source and a second operating characteristic of a second energy source are determinable. By means of the first energy source a first requirement share can be generated, and by means of the second energy source a second requirement share of the required means can be generated. The power regulating device can regulate the first energy source and the second energy source such that depending on the first operating characteristic and on the second operating characteristic the first requirement share and the second requirement share of the required means can be provided to the consumer.

Abstract: An energy control apparatus for controlling hybrid energy sources for an aircraft is designed for determining an operating characteristic of an energy source, a demand of at least one first consumer for a first resource and a demand of a second consumer for a second resource. The energy control apparatus activates the energy source in dependence on the demand for the first resource and the second resource and, if there is no demand for a first or second resource that is generatable by the energy source and is present in excess, supplies a third consumer with the excess resource. This makes it possible for an energy system to operate different consumers independently of the type of generated resources and their dependencies during the generation.

Abstract: A fire protection system for reducing the danger of fire, which has a fuel cell for producing a nitrogen-enriched cathode exhaust air. The fuel cell is supplied with air and a fuel. Within the fuel cell, the air is then reduced to a determined oxygen content. The exhaust air is supplied to the room to be protected.

Abstract: A fire protection system for reducing the danger of fire, which has a fuel cell for producing a nitrogen-enriched cathode exhaust air. The fuel cell is supplied with air and a fuel. Within the fuel cell, the air is then reduced to a determined oxygen content. The exhaust air is supplied to the room to be protected.

Abstract: A cooling system on board an aircraft includes a device for removing by suction a boundary layer, and a heat exchanger through which flows the boundary layer air that has been removed by suction. Cooling by way of a ram air channel can be reduced or entirely stopped, depending on the flight phase, such that the air drag of the aircraft and thus the fuel consumption can be reduced.

Abstract: The invention relates to an air conditioning system for a transportation means, having multiple zones to be air-conditioned, which may be variably air-conditioned by means of processed supply air in combination with individual trim air conduits, wherein the air conditioning system further has at least one heat exchanger for heating supply air by means of the exhaust heat of a fuel cell, and for discharging the supply air into a trim air distributor supplying the trim air conduits.

Abstract: A supply system for the energy supply in an aircraft comprising an engine for propelling an aircraft, a fuel cell for supplying an aircraft with electric energy, a first fuel reservoir for supplying the engine with engine fuel and a second fuel reservoir for supplying the fuel cell with fuel cell fuel. The first fuel reservoir is arranged separately of the second fuel reservoir.

Abstract: An aircraft fuel cell system (10) includes a fuel cell (12a, 12b, 12c, 12d) which has an oxidant inlet (14a, 14b, 14c, 14d) for supplying an oxygen-containing medium to the fuel cell (12a, 12b, 12c, 12d). An oxidant supply line (16) has a first end which is connected to the oxidant inlet (14a, 14b, 14c, 14d) of the fuel cell (12a, 12b, 12c, 12d). A second end of the oxidant supply line (16) is connectable to a used air outlet (18) of a cabin (20) of the aircraft.

Abstract: A fuel cell system for an aircraft is stated, which fuel cell system comprises a fuel cell unit and a suction module. The suction module is used to draw oxygen through the fuel cell unit. No vacuum generators are used during cruising flight.

Abstract: A power regulator and a process regulator, or a power regulating device for regulating hybrid energy sources are provided for an aircraft. The power regulator and process regulator is equipped such that the requirement of a required means of a consumer is measurable. In this arrangement the power regulating device is equipped such that a first operating characteristic of a first energy source and a second operating characteristic of a second energy source are determinable. By means of the first energy source a first requirement share can be generated, and by means of the second energy source a second requirement share of the required means can be generated. The power regulating device can regulate the first energy source and the second energy source such that depending on the first operating characteristic and on the second operating characteristic the first requirement share and the second requirement share of the required means can be provided to the consumer.

Abstract: A fire protection system for reducing the danger of fire, which has a fuel cell for producing a nitrogen-enriched cathode exhaust air. The fuel cell is supplied with air and a fuel. Within the fuel cell, the air is then reduced to a determined oxygen content. The exhaust air is supplied to the room to be protected.

Abstract: A fire fighting system for extinguishing a fire, which has a fuel cell for producing a nitrogen-enriched cathode exhaust air. The fuel cell is supplied with air and a fuel. Within the fuel cell, the air is then reduced to a determined oxygen content. The exhaust air is supplied to the fire source.

Abstract: The invention relates to a mixing system for inerting a gas volume. A first exhaust gas that is provided by a fuel cell, and a second exhaust gas that is provided by a hydrogen reformer, can be mixed to form an inert gas mixture. The mixture can be fed into the gas volume for inerting.

Abstract: A cooling system on board an aircraft includes a device for removing by suction a boundary layer, and a heat exchanger through which flows the boundary layer air that has been removed by suction. Cooling by way of a ram air channel can be reduced or entirely stopped, depending on the flight phase, such that the air drag of the aircraft and thus the fuel consumption can be reduced.

Abstract: A supply system for the energy supply in an aircraft comprising an engine for propelling an aircraft, a fuel cell for supplying an aircraft with electric energy, a first fuel reservoir for supplying the engine with engine fuel and a second fuel reservoir for supplying the fuel cell with fuel cell fuel. The first fuel reservoir is arranged separately of the second fuel reservoir.