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: Currently, the wastewater collection tank and the freshwater tanks comprise separate containers which are each mounted individually in the pressurized area of the cabin on the structure. In the present application a water-wastewater module is described which has two tanks for disposing of feces and wastewater and a water generation unit in the form of the fuel-cell module as integral components. The module and the fuselage may advantageously be manufactured separately from one another and first have to be combined during the final mounting of the aircraft.

Abstract: The present invention relates to a propulsion device for an aircraft. The propulsion device comprises a first energy converter (4), a second energy converter (5) and a propulsion unit (1). The first energy converter (4) provides first propulsion energy, and the second energy converter (5) provides second propulsion energy. The first energy converter (4) and the second energy converter (5) are adapted to provide the first propulsion energy and the second propulsion energy to the propulsion device (1).

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: 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: A replaceable cartridge for coupling to a consumer or to a filling station, wherein the replaceable cartridge comprises at least one disconnectable connection coupling for connection to the consumer or the filling station. Furthermore, the replaceable cartridge comprises a tank for holding liquid hydrogen.

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 module (10) for use in an aircraft (32) comprises at least one fuel cell system component (12, 22, 24). The fuel cell system module (10) is connectable modularly to a fuselage section (30) of the aircraft (32). A housing element (16, 26) of the fuel cell system module (10) is designed to form a section of an outer skin (34) of the aircraft (32) when the fuel cell system module (10) is in the state connected to the fuselage section (30) of the aircraft (32).

Abstract: A replaceable cartridge for coupling to a consumer or to a filling station, wherein the replaceable cartridge comprises at least one disconnectable connection coupling for connection to the consumer or the filling station. Furthermore, the replaceable cartridge comprises a tank for holding liquid hydrogen.

Abstract: A safety system for reducing the explosion risk of a fuel tank comprises a protective gas generating device and a delivery device for delivering the protective gas generated by the protective gas generating device into the fuel tank. The protective gas generating device (24) comprises a fuel cell system (26) having a fuel cell (28) and is configured so as to provide the delivery device (14) with a protective gas generated by the fuel cell (28) during operation of the fuel cell system (26).

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: An apparatus (10) for preparing meals, which is suitable in particular for use on board a commercial aircraft, includes a meal preparation unit (12) and a supply unit (14). The supply unit (12) includes a fuel cell system (16) having a fuel cell (18) and is equipped to supply the meal preparation unit (12) with water produced by the fuel cell (18).

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: The present invention relates to a propulsion device for an aircraft. The propulsion device comprises a propulsion unit and an energy converter. The energy converter is adapted for providing propulsion energy to the propulsion unit by a first fuel. Furthermore, the energy converter is adapted for providing propulsion energy to the propulsion unit by a second fuel. The propulsion unit adapted for generating forward thrust by the propulsion energy.

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: 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 drink dispenser which is particularly suitable for use on board a passenger plane, comprises a drink preparation unit and a supply unit. The supply unit has a fuel cell system with a fuel cell and is configured to supply the drink preparation unit with water, electric energy, and thermal energy produced by the fuel cell.