| Patent application number | Description | Published |
|---|
| 20090014593 | Cooling system on the basis of suction of a boundary layer - 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. | 01-15-2009 |
| 20090293494 | Hybrid drive for an aircraft - 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. | 12-03-2009 |
| 20090321090 | Fuel Cell System for Extinguishing Fires - 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. | 12-31-2009 |
| 20100018723 | Fire Protection With Fuel Cell Exhaust Air - 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. | 01-28-2010 |
| 20100071371 | POWER REGULATING DEVICE FOR AN AIRCRAFT - 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. | 03-25-2010 |
| 20100072318 | PROPULSION DEVICE FOR OPERATION WITH A PLURALITY OF FUELS FOR AN AIRCRAFT - 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. | 03-25-2010 |
| 20100170907 | DEVICE AND METHOD FOR STORING HYDROGEN FOR AN AIRCRAFT - 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. | 07-08-2010 |
| 20100316928 | Fuel Cell System Module - A fuel cell system module ( | 12-16-2010 |
| 20110041307 | REPLACEABLE CARTRIDGE FOR LIQUID HYDROGEN - 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. | 02-24-2011 |
| 20110045370 | Aircraft Fuel Cell System - An aircraft fuel cell system ( | 02-24-2011 |
| 20110095128 | AIRCRAFT WITH AT LEAST TWO RUDDER UNITS IN A NON CENTRAL ARRANGEMENT - 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. | 04-28-2011 |
| 20110095136 | AIRCRAFT WITH VERTICAL STABILIZERS ARRANGED ON A CENTRAL FUSELAGE BODY AND METHOD, AS WELL AS CONTROL UNIT, FOR COMPENSATING A NEGATIVE PITCHING MOMENT - 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. | 04-28-2011 |
| 20110101166 | CONTROL UNIT AND METHOD FOR CONTROLLING THE SUPPLY OF A VEHICLE WITH MULTIPLE FUELS - 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. | 05-05-2011 |
| 20110108663 | PROPULSION DEVICE WITH A PLURALITY OF ENERGY CONVERTERS FOR AN AIRCRAFT - The present invention relates to a propulsion device for an aircraft. The propulsion device comprises a first energy converter ( | 05-12-2011 |
