Abstract: A method for controlling the pressure and/or the flow rate of a fluid includes withdrawing flow energy from a fluid flowing through a pipeline (15). This energy is converted at least partially into electrical energy and used for the electrical control (65) of the flow rate and/or the pressure of a fluid. The device for controlling the flow rate and/or pressure of a fluid in a pipeline (20) has at least one electric generator (35), which is developed for the withdrawal of flow energy from a flowing fluid and for converting this energy at least partially into electrical energy. The device has a control mechanism (65) for controlling the flow rate and/or pressure of a fluid in a pipeline (20) with an electric driving mechanism supplied by the generator (35).

Abstract: The invention relates to a passenger oxygen mask for the emergency supply of oxygen in an aircraft, with a breathing bag which is provided on the entry side with a tube for the oxygen supply, wherein the tube and the breathing bag consist of polyurethane. The invention further relates to a breathing bag, with which a flow indicator is integrated into the connection piece.

Abstract: An arrangement of at least one personal service unit in a vehicle. At least one rail is arranged on the vehicle side. The rail includes at least one lead. The personal service unit includes at least one electricity collector which is arranged in a manner such that the electricity collector conductively contacts the at least one lead of the rail in the installed condition of the personal service unit in the vehicle.

Abstract: A cockpit oxygen supply device includes at least one oxygen mask which is conductively connectable to an oxygen tank, wherein at least one throughput measurement device is arranged in the flow path of the device. A breathing activity of the pilot and/or an undesired outflow from the mask may be recognized with the help of an evaluation device.

Abstract: A passenger oxygen mask includes a carrier body and an annular holder which is provided on the carrier body and which is with an opening for fastening a pull device. A slot through which the pull device can be introduced into the opening is provided in the annular holder.

Abstract: An emergency oxygen supply device for an aircraft comprises an oxygen pressure tank, and at least one oxygen mask which is conductively connected thereto. At least two electrically actuatable and activatable shut-off valves which are arranged parallel to one another are arranged in the conduit from the oxygen pressure tank to the at least one oxygen mask. Of these shut-off valves, at least one shut-off valve has an NO-function and at least one shut-off valve an NC-function.

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 cockpit oxygen mask includes a mask body, an oxygen inhalation valve, a mixed air inhalation valve, an exhalation valve as well as 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 includes 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 includes at least one discontinuous location which deforms a magnetic field produced in the wall.

Abstract: A cockpit oxygen mask includes a mask body, an oxygen inhalation valve, a mixed air inhalation valve, an exhalation valve as well as 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 includes at least one through flow path which may be closed by a magnetically movable valve body, wherein the through flow path is limited by a magnetizable wall, and wherein the wall includes at least one discontinuous location which deforms a magnetic field produced in the wall.

Abstract: A method is provided for emergency supply of oxygen in an aircraft. First, stored oxygen is led to the oxygen masks of the aircraft occupants, and simultaneously a part of the stored oxygen is used for flushing molecular sieve beds of an air decomposition device, at the beginning of the emergency supply. Subsequently, the air decomposition device assumes the oxygen supply to the aircraft occupants.

Abstract: A method for controlling the pressure and/or the flow rate of a fluid includes withdrawing flow energy from a fluid flowing through a pipeline (15). This energy is converted at least partially into electrical energy and used for the electrical control (65) of the flow rate and/or the pressure of a fluid. The device for controlling the flow rate and/or pressure of a fluid in a pipeline (20) has at least one electric generator (35), which is developed for the withdrawal of flow energy from a flowing fluid and for converting this energy at least partially into electrical energy. The device has a control mechanism (65) for controlling the flow rate and/or pressure of a fluid in a pipeline (20) with an electric driving mechanism supplied by the generator (35).

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.