Abstract: An emergency oxygen supply system, particularly in an aircraft, has an oxygen supply conduit with a conduit junction. This conduit junction is formed by a valve, which forms a flow path from an oxygen inlet to two oxygen outlets, wherein the valve is designed in a manner such that one of the oxygen outlets may be selectively closed.

Abstract: A pressure regulation device is provided, in particular for an oxygen emergency supply system in an aircraft. The device includes at least two parallel conduits in each of which at least two controllable valves are arranged in series. Further, a pressure sensor is arranged on the exit side of the valve arrangement, for the detection of the actual pressure value, and a controller is provided, which is signal-connected to the pressure sensor and controls the valves.

Abstract: A cockpit oxygen mask comprises a mask body, an oxygen inhalation valve, a mixed air inhalation valve, an exhalation valve as well as with a control device. At least the oxygen inhalation valve is signal-connected to the control device. The oxygen inhalation valve is designed as an electromagnetically actuatable valve, and comprises at least one throughflow path which may be closed by a magnetically movable valve body, wherein the throughflow path is limited by a magnetizable wall, and wherein the wall comprises at least one discontinuous location which deforms a magnetic field produced in the wall.

Abstract: An oxygen emergency supply device for an aircraft includes an oxygen pressure vessel, which is in fluid connection with at least one oxygen mask. Means for closing and opening the oxygen pressure vessel, means for pressure reduction, a pressure regulation device, and a flow throttle are provided in the conduit connection between the oxygen pressure vessel and the oxygen mask. The oxygen emergency supply device further includes a control device. A controllable shut-off valve forms the means for closing and opening the oxygen pressure vessel, the means for pressure reduction and a part of the pressure regulation device.

Abstract: A device for enriching air with oxygen in an aircraft, and a method for operating the device provides product gas enrichment with oxygen with minimum requirements. An oxygen measurement apparatus analyzing the product gas flow as well as a throughput sensor are provided in combination with a change-over device. A flow connection to an outlet channel is created in a first switch position, and a flow connection to a consumer conduit exists in a second switch position. A device for producing a change-over signal from the first switch position to the second switch position is provided if the determined oxygen output as a product of the product gas flow and the oxygen concentration has reached or exceeded a predefined threshold value.

Abstract: An air exit guidance which in particular is provided for arrangement in the personal service unit of an passenger aircraft. The guidance includes an air inlet and an air outlet as well as an adjustable throttle which is arranged at the inflow side of the air exit guidance.

Abstract: The method serves for operating an air fractionization installation for obtaining oxygen on board an aircraft, with at least two molecular sieve chambers. A part mass flow of the oxygen obtained in the respective adsorbing molecular sieve chamber is supplied for flushing a desorbing molecular sieve chamber. The quantity of the flushing oxygen led to the desorbing molecular sieve chamber is controlled by way of this.

Abstract: A safety device is provided for a gas distribution system in an airplane, containing at least one pressure regulator (5) between a pressurized gas source (2) and a supply line. Reliability of operation is improved with the provision of a pressure-limiting device (4) with two lines (41, 42) arranged in parallel with two pressure-limiting valves (43, 44, 45, 46) each arranged in the same direction in series. The pressure-limiting device (4) is arranged upstream of the pressure regulator (5).

Abstract: A passenger oxygen mask for an aircraft with a mask body which is to come to bear on the face in a use situation and which engages over of the mouth and nose in the correct position of use. A lead-through for a drinking tube is provided.

Abstract: An aircraft, aircraft system and air fractionization device are provided. The air fractionization device is provided for use on board an aircraft. The air fractionization installation functions according to the principle of pressure swing adsorption and is supplied by the air conditioning and pressurization system with which also the aircraft cabin may be supplied with air.

Abstract: A passenger oxygen mask with a flexible mask body with at least one section of the mask body which is designed plastically deformable or is provided for accommodating a plastically deformable support element.

Abstract: A device for enriching air with oxygen by pressure swing adsorption in a molecular sieve bed provides for the separation of water from the air to be enriched with oxygen. The water separator is arranged directly upstream of the molecular sieve bed (8). The water separator is designed as a cyclone type water separator (5).

Abstract: A gas distribution system in an airplane has improved reliability of operation with a first supply line (7) and a second supply line (9) for pressurized gas connected to a pressurized gas source (2) via a branching site (6) with a second shut-off valve (10). The pressure in the supply lines (7, 9) is determined with a pressure-measuring means (24). An evaluating device (24) for the measured pressure signal is provided for sending a closing signal to the shut-off valve (8, 10) of the supply line (7, 9) in which a pressure drop of consequence occurs.

Abstract: The passenger oxygen mask is provided for emergency situations on board an aircraft. The mask body is designed collapsible at least in sections. An axial overall height of the mask body is reduced by way of the one or more mask sections. This simplifies the accommodation of the oxygen mask or even permits a smaller constructional size of the preparation device.

Abstract: A device for enriching air with oxygen in an aircraft, and a method for operating the device provides product gas enrichment with oxygen with minimum requirements. An oxygen measurement apparatus analyzing the product gas flow as well as a throughput sensor are provided in combination with a change-over device. A flow connection to an outlet channel is created in a first switch position, and a flow connection to a consumer conduit exists in a second switch position. A device for producing a change-over signal from the first switch position to the second switch position is provided if the determined oxygen output as a product of the product gas flow and the oxygen concentration has reached or exceeded a predefined threshold value.

Abstract: An emergency oxygen supply system for an aircraft provides that oxygen may be made available additionally to the breathing gas supply which is brought along on board the aircraft. A gas distribution system supplies breathing masks with oxygen from one of a first oxygen source in the form of a pressurized gas source or a chemical oxygen generator. A second oxygen source is in the form of a molecular sieve bed arrangement. A change-over device selectively connects the gas distribution system to the first oxygen source or to the second oxygen source. A measurement probe delivers a status signal corresponding to a predefined flight altitude. A control unit delivers a change-over signal from the first oxygen source to the second oxygen source to the change-over device given the presence of the status signal.

Abstract: A device for enriching air with oxygen by pressure swing adsorption in a molecular sieve bed provides for the separation of water from the air to be enriched with oxygen. The water separator is arranged directly upstream of the molecular sieve bed (8). The water separator is designed as a cyclone type water separator (5).

Abstract: An apparatus for supplying respiratory gas to a parachute jumper includes a mask which can be worn by the parachute jumper and a first respiratory gas reservoir includes a pressurized-gas vessel containing respiratory gas. The pressurized-gas vessel has an adjustable metering valve for metering respiratory gas contained in the pressurized vessel. A breathing hose connects the metering valve to the mask for conducting the respiratory gas to the mask. A second respiratory-gas reservoir contains a solid-state oxygen generator and has a manually-actuable starting device for the solid-state oxygen generator. The second respiratory-gas reservoir is connected to the breathing hose.

Abstract: A modular oxygen supply system is provided comprising at least one module skeleton with a baseplate with frames arranged in parallel to one another. The system includes supply lines for ambient air with air connections for taking off the air, first gas lines for oxygen with first gas connections for taking up the oxygen and second gas lines for outgoing air with second gas connections for taking up outgoing air. Rack guides with data lines are provided. At least one individual module can be pushed into the module skeleton. Each individual module has at least one molecular sieve container fastened on a baseplate with the gas connections and with an electric contact. Each individual module has a gas treatment unit for the ambient air fed in. A pressure reducer and a multiple-way valve as well as an oxygen reservoir are arranged downstream of the molecular sieve container or containers connected in parallel.

Abstract: A gas distribution system in an airplane has improved reliability of operation with a first supply line (7) and a second supply line (9) for pressurized gas connected to a pressurized gas source (2) via a branching site (6) with a second shut-off valve (10). The pressure in the supply lines (7, 9) is determined with a pressure-measuring means (24). An evaluating device (24) for the measured pressure signal is provided for sending a closing signal to the shut-off valve (8, 10) of the supply line (7, 9) in which a pressure drop of consequence occurs.