Abstract: A system for reducing harmful substances in engine exhaust gases includes a fuel cell, which is adapted to generate electrical energy and a steam-containing fuel cell exhaust gas during operation. A fuel tank serves to store fuel which is to be supplied to an engine during operation. A condensing device is connected to an exhaust gas outlet of the fuel cell so that steam-containing fuel cell exhaust gas is supplyable to the condensing device. The condensing device is adapted to convert the steam contained in the fuel cell exhaust gas into the liquid state of aggregation by means of condensation and to introduce the water obtained as a result of the condensing process into the fuel in order to form a water/fuel mixture. A water/fuel mixture line is connected to the engine so that a water/fuel mixture is supplyable to the engine.

Abstract: A cooling assembly for cooling a thermal body for an aircraft. The cooling assembly has a Peltier element with a hot side and a cold side. Furthermore, the cooling assembly has a thermal body. The thermal body is arranged in heat-conductive contact with the cold side of the Peltier element. The hot side of the Peltier element is adapted to dissipate thermal energy to an aircraft structure, such that the thermal body may be cooled.

Abstract: A drive device for an aircraft comprises a gas turbine apparatus for generating a first drive energy and electric motor for generating a second drive energy. The gas turbine apparatus and the electric motor are set up in such a way that the drive unit may be provided with at least one of the first drive energy and the second drive energy. The drive unit is set up to generate propulsion using at least one of the first drive energy and the second drive energy.

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 device and a method for controlling the air humidity in a fuel cell detect a step response in the output voltage of a fuel cell when the supply to electrical loads is interrupted, and determine parameters of the dynamic time characteristic from the detected step response, and thus calculate a capacitance of the fuel cell. As a function of any deviation from a predetermined capacitance, a humidity control unit is caused to increase or decrease the humidity. This makes in situ detection of the humidity balance of a fuel cell possible, and this can keep the electrical power thereof constant for a relatively long period, and this can increase the intervals between maintenance.

Abstract: A cooling system for cooling a fuel-cell system on board an aircraft, in one example, includes a hydrogen accumulator, a connecting device coupling the hydrogen accumulator, with an external cooling system for dissipating heat arising upon charging of the hydrogen accumulator. The hydrogen accumulator cools down upon removal of hydrogen, because of which cooling of a condenser occurs. The cooling system need not utilize a secondary cooling loop for condenser cooling.

Abstract: A device and a method for controlling the air humidity in a fuel cell detect a step response in the output voltage of a fuel cell when the supply to electrical loads is interrupted, and determine parameters of the dynamic time characteristic from the detected step response, and thus calculate a capacitance of the fuel cell. As a function of any deviation from a predetermined capacitance, a humidity control unit is caused to increase or decrease the humidity. This makes in situ detection of the humidity balance of a fuel cell possible, and this can keep the electrical power thereof constant for a relatively long period, and this can increase the intervals between maintenance.

Abstract: A sanitary device for autonomous operation for a conveyance. The sanitary device has a sanitary module and a supply system. The sanitary module is set up replaceably in a cabin area of the conveyance. The supply system is set up in the sanitary module to supply it. The sanitary module is autonomously operable.

Abstract: A system for generating energy for a consumer element in an aircraft includes the consumer element with a fuel cell element and a rechargeable metal hydride storage cell. The rechargeable metal hydride storage cell is designed for supplying the fuel cell element with hydrogen such that energy can be generated for the consumer element. The rechargeable metal hydride storage cell is furthermore designed in such a way that it can be charged with hydrogen.

Abstract: A sorting device and a method for sorting goods in transit for an aircraft are disclosed. The sorting device includes a sorting region with a sorting unit and a storage region. The sorting region is adapted such that goods in transit are capable of being provided to the sorting region in an undetermined first arrangement. The sorting region includes a longitudinal axis, where a sorting unit may be moved along the longitudinal axis of the sorting region. The sorting unit is capable of sorting the goods in transit from an undetermined first arrangement to a predetermined second arrangement, where the goods in transit may be provided in the predetermined second arrangement in the storage region.

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: A system (10) for reducing harmful substances in engine exhaust gases comprises a fuel cell (12), which is adapted to generate electrical energy and a steam-containing fuel cell exhaust gas during operation. A fuel tank (38) serves to store fuel which is to be supplied to an engine (44) during operation. A condensing device (32) is connected to an exhaust gas outlet (16) of the fuel cell (12) so that steam-containing fuel cell exhaust gas is supplyable to the condensing device (32). The condensing device (32) is adapted to convert the steam contained in the fuel cell exhaust gas into the liquid state of aggregation by means of condensation and to introduce the water obtained as a result of the condensing process into the fuel in order to form a water/fuel mixture. A water/fuel mixture line (96) is connected to the engine (44) so that a water/fuel mixture is supplyable to the engine (44).

Abstract: For operation, PEMFCs require among other things a compressor for the cathode air, and a system for removing the water which is generated on the cathode side as a result of the electrochemical reaction. According to an embodiment of the present invention the removal of water is supported in that the fuel cell is made to rotate by way of an electric motor so that the water contained in the cathodes of the fuel cell can be extracted by centrifugal force. To this effect the air channels on the cathode side are arranged so as to extend radially or in a spiral shape from the inside towards the outside. In this way the efficiency of the fuel cell can be significantly improved.

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 passenger seat has autonomous electric power generated by a fuel cell system and humidification provided by the fuel cell system. The fuel cell system may include replaceable fuel cartridges and may power electronics such as in flight entertainment, lighting, comfort features, seat adjustments, communications and other features autonomously or under control of the seat occupant.

Abstract: A fuel cell system comprises a combination of a first fuel cell of a first type and a second fuel cell of a second type, arranged downstream of the first fuel cell. The anode side of the first fuel cell is coupled with a cathode side of the second fuel cell; allowing the purge gas emanating from the first fuel cell to be fed to the cathode side of the second fuel chamber, rather than to outside air.

Abstract: A cooling system for cooling a fuel-cell system on board an aircraft, in one example, includes a hydrogen accumulator, a connecting device coupling the hydrogen accumulator, with an external cooling system for dissipating heat arising upon charging of the hydrogen accumulator. The hydrogen accumulator cools down upon removal of hydrogen, because of which cooling of a condenser occurs. The cooling system need not utilize a secondary cooling loop for condenser cooling.

Abstract: A cooling assembly for cooling a thermal body for an aircraft. The cooling assembly has a Peltier element with a hot side and a cold side. Furthermore, the cooling assembly has a thermal body. The thermal body is arranged in heat-conductive contact with the cold side of the Peltier element. The hot side of the Peltier element is adapted to dissipate thermal energy to an aircraft structure, such that the thermal body may be cooled.

Abstract: A drive device for an aircraft comprises a gas turbine apparatus for generating a first drive energy and electric motor for generating a second drive energy. The gas turbine apparatus and the electric motor are set up in such a way that the drive unit may be provided with at least one of the first drive energy and the second drive energy. The drive unit is set up to generate propulsion using at least one of the first drive energy and the second drive energy.

Abstract: Drain masts of commercial aircraft need to be heated in order to prevent freezing caused by the low outside temperatures when the aircraft travels at a corresponding altitude. An exemplary embodiment described in the application pertains to a drain system for an aircraft that can be used for draining liquids or gases from the aircraft or for drawing air into the aircraft. In this case, the liquids or gases are heated by means of a coolant that receives its thermal energy from a thermal or electrochemical process being carried out on board the aircraft. Consequently, the waste heat produced by the thermal or electrochemical process being carried out on board the aircraft, for example, a fuel cell process, can be carried off outboard via the drain system. In addition, the coolant can be advantageously utilized for cooling the thermal or electrochemical process.