Abstract: An autarkic monument in an aircraft pressure cabin supplied with the required operating mediums in a decentralized fashion by carrying along these operating mediums in the monument in operating medium reservoirs is provided. Methods for the efficient energy conversion within this autarkic monument are also provided. The efficiency is achieved such that the energy conversion is, based on the operating mediums, optimized with respect to exergo-economic and/or exergo-ecologic aspects, and such that energy conversion processes are adapted to one another if several energy conversion processes take place.

Abstract: The present disclosure relates to a hydrogen-storage device and a method for releasing hydrogen from the hydrogen-storage device. Moreover, the disclosure relates to an energy-producing device and an aircraft having the hydrogen-storage device and/or the energy-producing device. According to the disclosure, a hydrogen-storage device is provided. The hydrogen-storage device includes an outer coating, an inner core material and a hydrogen releasing interface in the outer coating. The inner core material includes a composite containing a matrix material having porous carbon-containing material and a hydrogen-storage material having chemically bonded hydrogen.

Abstract: The present disclosure relates to a composite having a porous graphene oxide material (A) and ammonia borane (B), wherein the porous graphene oxide material (A) has a density of 1-100 mg/cm3, and a method for producing the same. The disclosure also relates to a hydrogen-releasing device having the disclosed composite as well as to an energy-producing device having the disclosed composite. Moreover, the disclosure relates to an aircraft having the hydrogen-releasing device and/or the energy-producing device.

Abstract: A galley system comprises at least one electrically operated galley device, at least one fuel cell, a plurality of compartments for housing the galley devices, and an air extraction means. At least one of the plurality of compartments comprises at least one air extraction port couplable with the air extraction means. The at least one compartment is adapted for housing at least one of the at least one fuel cell and for removing at least a part of heat emanated from the at least one fuel cell through the air extraction means. At least one of the at least one electrically operated galley device is electrically couplable with the at least one fuel cell unit.

Abstract: A galley system comprises at least one electrically operated galley device, at least one fuel cell, a plurality of compartments for housing the galley devices, and an air extraction means. At least one of the plurality of compartments comprises at least one air extraction port couplable with the air extraction means. The at least one compartment is adapted for housing at least one of the at least one fuel cell and for removing at least a part of heat emanated from the at least one fuel cell through the air extraction means. At least one of the at least one electrically operated galley device is electrically couplable with the at least one fuel cell unit.

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 module for use in an aircraft includes at least one fuel cell system component. The fuel cell system module is connectable modularly to a fuselage section of the aircraft. A housing element of the fuel cell system module is designed to form a section of an outer skin of the aircraft when the fuel cell system module is in the state connected to the fuselage section of the aircraft.

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: 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: 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: An autarkic monument in an aircraft pressure cabin supplied with the required operating mediums in a decentralized fashion by carrying along these operating mediums in the monument in operating medium reservoirs is provided. Methods for the efficient energy conversion within this autarkic monument are also provided. The efficiency is achieved such that the energy conversion is, based on the operating mediums, optimized with respect to exergo-economic and/or exergo-ecologic aspects, and such that energy conversion processes are adapted to one another if several energy conversion processes take place.

Abstract: An aircraft includes, but is not limited to a central fuselage body without horizontal stabilizer, at least one high-lift control surface, at least one vertical stabilizer that is arranged on the central fuselage body and at least one extendable compensation control surface. The compensation control surface may be moved independently of the high-lift control surface of the aircraft and generates a positive tail-heavy pitching moment when it is moved into the flow against the aircraft. Due to this measure, a negative pitching moment during the actuation of high-lift control surfaces may be at least partially eliminated without influencing the high lift. Rudder segments that may be moved opposite to one another on two vertical stabilizers that are arranged mirror-symmetrical referred to the longitudinal axis of the aircraft preferably are used for this purpose.

Abstract: An aircraft has at least two rudder units in a non-central arrangement. The rudder units have a profile and are rigidly secured to the aircraft. The profile is adjusted in such a way as to yield an inflow at a positive geometric angle of incidence, so that the profile generates a lift force having a component pointing in the flight direction. This makes it possible to offset a portion of the aircraft drag.

Abstract: The present invention relates to a tank device for storing hydrogen for an aircraft. The tank device comprises an outer tank and an inner tank. The inner tank is held in the outer tank. The outer tank is arranged such that the hydrogen with first physical characteristics can be stored. The inner tank is designed such that the hydrogen with second physical characteristics can be stored. The outer tank is connected to the inner tank such that the hydrogen can be fed to the inner tank from the outer tank. The inner tank is designed such that the hydrogen with the first physical characteristics can be converted to the hydrogen with second physical characteristics. The inner tank is arranged such that the hydrogen comprising the second physical characteristics can be fed to a consumer.

Abstract: A control unit for controlling the supply of a vehicle having at least one internal combustion engine with multiple fuels has at least one input means for supplying optimization parameters, fuel parameters, and operational data, at least one storage unit for storing the optimization parameters, the fuel parameters, and the operational data, and at least one computing unit. The control unit is adapted for being connected to at least one first supply apparatus for supplying a first fuel to the internal combustion engine and to at least one second supply apparatus for supplying a second fuel to the internal combustion engine, and of controlling a first mass flow of supplied first fuel and a second mass flow of supplied second fuel. The computing unit optimizes the ratio of first mass flow and second mass flow for all operational phases of the vehicle to fulfill the specified optimization parameters.

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: The present invention relates to a tank device for storing hydrogen for an aircraft. The tank device comprises an outer tank and an inner tank. The inner tank is held in the outer tank. The outer tank is arranged such that the hydrogen with first physical characteristics can be stored. The inner tank is designed such that the hydrogen with second physical characteristics can be stored. The outer tank is connected to the inner tank such that the hydrogen can be fed to the inner tank from the outer tank. The inner tank is designed such that the hydrogen with the first physical characteristics can be converted to the hydrogen with second physical characteristics. The inner tank is arranged such that the hydrogen comprising the second physical characteristics can be fed to a 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 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.