Abstract: The present invention provides an inhalation device which has two pumps, one providing a nebulizer flow and the other providing a support flow. The nebulizer flow passes through a nebulizing nozzle to generate an aerosol flow from a liquid. The aerosol flow and the support flow are combined to provide a total flow through a mouthpiece to a patient. The device can be configured specifically for pediatric use by removing the support flow pump. The invention also provides a method of providing a flow of aerosol and / or air to a patient using the device, in particular a device which provides a defined volume of air and aerosol as a bolus at a defined flow rate on each inhalation.

Abstract: A method for operating a rocket propulsion system comprises the steps of supplying oxygen to a combustion chamber, supplying hydrogen to the combustion chamber and combusting the oxygen-hydrogen mixture in the combustion chamber. The rocket propulsion system is operated alternately in a first operating mode, in which oxygen and hydrogen are supplied to the combustion chamber in a first mass mixing ratio of oxygen to hydrogen, and in a second operating mode, in which oxygen and hydrogen are supplied to the combustion chamber in a second mass mixing ratio of oxygen to hydrogen that is greater than the first mass mixing ratio.

Abstract: A rocket propulsion system comprises a combustion chamber, an oxygen supply system, comprising an oxygen supply duct and being configured to supply oxygen to the combustion chamber, and a hydrogen supply system, comprising a hydrogen supply duct and being configured to supply hydrogen to the combustion chamber. An ignition unit of the propulsion system, to which at least portions of the oxygen and the hydrogen supplied to the combustion chamber can be supplied, is configured to initiate combustion of the oxygen-hydrogen mixture in the combustion chamber. The propulsion system further comprises a cooling duct extending along an inner surface of a combustion chamber wall and through which at least a portion of the oxygen supplied to the combustion chamber, at least a portion of the hydrogen supplied to the combustion chamber or a combustion gas mixture emerging from the ignition unit flows.

Abstract: A thrust nozzle, in particular thrust nozzle for a rocket engine, with a convergent wall section, a throat section and a divergent wall section. The divergent wall section has a first region adjacent to the throat section, the wall contour of which region corresponds to a truncated ideal nozzle, and the divergent wall section has a second region facing away from the throat section, which region has a wall contour deviating from the first region.

Abstract: A rocket propulsion system comprises a combustion chamber, an oxygen supply system, comprising an oxygen supply duct and being configured to supply oxygen to the combustion chamber, and a hydrogen supply system, comprising a hydrogen supply duct and being configured to supply hydrogen to the combustion chamber. An ignition unit of the propulsion system, to which at least portions of the oxygen and the hydrogen supplied to the combustion chamber can be supplied, is configured to initiate combustion of the oxygen-hydrogen mixture in the combustion chamber. The propulsion system further comprises a cooling duct extending along an inner surface of a combustion chamber wall and through which at least a portion of the oxygen supplied to the combustion chamber, at least a portion of the hydrogen supplied to the combustion chamber or a combustion gas mixture emerging from the ignition unit flows.

Abstract: A method for operating a rocket propulsion system comprises the steps of supplying oxygen to a combustion chamber, supplying hydrogen to the combustion chamber and combusting the oxygen-hydrogen mixture in the combustion chamber. The rocket propulsion system is operated alternately in a first operating mode, in which oxygen and hydrogen are supplied to the combustion chamber in a first mass mixing ratio of oxygen to hydrogen, and in a second operating mode, in which oxygen and hydrogen are supplied to the combustion chamber in a second mass mixing ratio of oxygen to hydrogen that is greater than the first mass mixing ratio.

Abstract: A thrust nozzle, in particular thrust nozzle for a rocket engine, with a convergent wall section, a throat section and a divergent wall section. The divergent wall section has a first region adjacent to the throat section, the wall contour of which region corresponds to a truncated ideal nozzle, and the divergent wall section has a second region facing away from the throat section, which region has a wall contour deviating from the first region.

Abstract: The present invention relates to a device for providing an aerosol flow, an air flow or both with at least a compressor for providing an air flow, a nebulization device for generating an aerosol flow and a mixing means for optionally mixing the aerosol flow with the air flow to provide a total flow, wherein the total flow is composed of the aerosol flow, the air flow or both. Further, the device comprises at least a first air channel between the compressor and the nebulization device, at least a second air channel between the compressor and the mixing means and an amplification means for increasing the air flow provided by the compressor.

Abstract: The present invention relates to a device for providing an aerosol flow, an air flow or both with at least a compressor for providing an air flow, a nebulization device for generating an aerosol flow and a mixing means for optionally mixing the aerosol flow with the air flow to provide a total flow, wherein the total flow is composed of the aerosol flow, the air flow or both. Further, the device comprises at least a first air channel between the compressor and the nebulization device, at least a second air channel between the compressor and the mixing means and an amplification means for increasing the air flow provided by the compressor.