Abstract: The valve actuator (1) includes a housing (2), a motor (4) coupled to the valve, wherein rotation of the motor (4) changes the position of the valve from a first position in which fluid flow may occur along at least one path and a second position in which fluid flow is either blocked or may occur along at least one second path, said motor (4) being normally supplied with electrical power from a main source of electrical power, at least one sensor (24,132) configured to detect the position of the valve and/or the valve speed, a switch (16) controlling the delivery of electrical power to the motor (4), and a power circuitry (19) connected to the switch (16).

Abstract: A breathing assembly for aircraft comprising a storage unit, a breathing mask and a releasable securing device. The storage unit has a guiding surface extending perpendicularly to an elevation direction and a maintaining element. The breathing mask comprises a rigid support having a sliding surface adapted to slide in contact with the guiding surface of the storage unit, along a sliding direction between a storage position and an exit position. The support further has a maintaining element. In the storage position, the sliding surface of the support is prevented from moving away from the guiding surface of the storage unit along the elevation direction at the distal end by engagement of the maintaining element of the support with the maintaining element of the storage unit.

Abstract: A liquid sensor system can detect whether liquid is present at a location within a tank or other container, such as an aircraft fuel tank. The system can include a sensor that has a heated negative temperature coefficient (NTC) element and a temperature compensator element. The sensor may be located within the tank. The elements can be polarized by voltages from separate voltage sources. The voltages can be compared to detect a presence or level of liquid within the tank. Only two wires may be needed to connect the sensor with components outside the tank. The system may be able to detect liquid using less than twenty five milliamps and a sensor temperature that is less than two hundred degrees Celsius.

Abstract: The invention relates to a method and an emergency oxygen supply mask adapted for rescuing a passenger of an aircraft in an emergency situation. In one example, the oxygen mask includes a mask body with a first opening for covering the mouth and/or nose of a passenger and with a second opening connecting the first opening for providing breathable supply air. In some cases, the emergency oxygen supply mask includes a physical reaction component connected to the mask body for receiving air and converting the air into supply air by a physical reaction between the air and a physical reaction material in the physical reaction component to produce oxygen-enriched air. The oxygen-enriched air may be supplied as the supply air to the first opening of the mask body.

Abstract: Detailed is an aircraft oxygen emergency device including a chemical oxygen generator, an oxygen supply line including a first line section connecting the chemical oxygen generator with a flow regulator unit, and a second line section connecting the flow regulator unit with at least one oxygen mask for supplying oxygen to a mouth or a nose (or both) of a person at a breathing pressure.

Abstract: This invention relates to cabin service arrangement assigned to at least one passenger seat in a seat row of an aircraft, comprising: a lighting unit for providing a light projection and at least one man machine interface for operating the lighting unit, wherein the at least one man machine interface is associated with an initiating unit for providing an activation of the lighting unit and a deactivation unit for receiving an indication for deactivation of the light projection, wherein the deactivation is initializable by an external signal, and wherein the light projection from the lighting unit comprises an illumination, the illumination being adapted to effect a cabin attendant call. According to the invention the illumination is adapted to be projected to a projection spot outside of the seat row, and the deactivation of the illumination is effectable from outside of the seat row.

Abstract: Described are lighting devices of passenger aircraft. Also described are methods of operating the devices as well as lighting systems and passenger service units.

Abstract: A liquid sensor system can detect whether liquid is present at a location within a tank or other container, such as an aircraft fuel tank. The system can include a sensor that has a heated negative temperature coefficient (NTC) element and a temperature compensator element. The sensor may be located within the tank. The elements can be polarized by voltages from separate voltage sources. The voltages can be compared to detect a presence or level of liquid within the tank. Only two wires may be needed to connect the sensor with components outside the tank. The system may be able to detect liquid using less than twenty five milliamps and a sensor temperature that is less than two hundred degrees Celsius.

Abstract: Oxygen regulator (1) to deliver breathing gas in a cabin (10) of an aircraft comprising a first inlet (12) for pressurized breathing oxygen, a second inlet (14) for diluter gas, an outlet (16) to provide a breathing mixture to a user, and a regulation device adjusting the concentration of breathing oxygen in the breathing mixture. The regulation device comprises a emergency device (30) that adjusts the concentration of breathing oxygen in the breathing mixture as a function of a variation speed of the cabin altitude.

Abstract: The invention relates to an emergency tubing set, including an oxygen mask adapted to cover a users mouth and nose, a tubing connected at a first end to said tubing set to provide oxygen to said oxygen mask, and a connect or connected to said tubing at a second end opposed to said first end, the connector being adapted to be connected to an oxygen source for supplying oxygen to said tubing. According to the invention the tubing includes an excess tubing section and a connecting tubing section wherein the excess tubing section is stored in a bottom pouch and a first part of an intermediate tubing section is arranged inside the bottom pouch and a second part of said intermediate tubing section is arranged outside said bottom pouch, wherein the intermediate tubing interconnects the excess tubing section and the connecting tubing section.

Abstract: Described is an oxygen breathing device, including a casing, the casing accommodating, in a non-activated condition, an oxygen source, in particular a chemical oxygen generator or an oxygen pressure tank, a starter device for initiating a flow of oxygen out of the oxygen source, a buffer connected to the oxygen source, the buffer being adapted to temporarily store oxygen produced in the oxygen source, at least one oxygen mask connected via an oxygen supply line to the buffer wherein a flexible buffer is provided in the oxygen breathing device and connected to the oxygen source.

Abstract: The present invention relates to an oxygen breathing device, in particular for providing oxygen to passengers or crew of an aircraft, the device comprising an oxygen source for providing pressurized oxygen, a valve connected to the oxygen source via a pressure line, a control unit for controlling said valve, and at least one nozzle for dispensing the oxygen passing through said valve. In particular, the present invention relates to an oxygen breathing device comprising a measuring unit for determining the mass flow rate of oxygen passing through said nozzle. Furthermore, the invention relates to a method for supplying oxygen to a person, in particular a flight passenger, using an oxygen breathing device.

Abstract: The invention relates to an oxygen breathing device that includes an oxygen source, in particular a chemical oxygen generator or an oxygen pressure tank, at least one oxygen mask connected via an oxygen supply line to said oxygen source, and a flow control unit adapted to receive a signal indicating ambient pressure or to detect ambient pressure and to control the flow of oxygen through the oxygen supply line depending on said ambient pressure. In some embodiments, the flow control unit is adapted to provide a low oxygen flow at a first ambient pressure and provide a higher oxygen flow at a second ambient pressure which is lower than said first ambient pressure.

Abstract: Embodiments of the invention relate to a chemical oxygen generator for an emergency oxygen device, comprising an outer housing defining an interior space and comprising an outlet opening, a solid oxygen source within said interior space containing a material which is able to produce oxygen in a chemical reaction. According to embodiments of the invention, a hollow tube within said interior space is embedded in said solid oxygen source.

Abstract: Embodiments of the present invention relate generally to removable storage for hydrogen networks on-board an aircraft, aerospace vehicles, or other passenger transport vehicles. They are particularly related to such vehicles that use a hydrogen network in order to support a fuel cell system, more scecifically it discloses an interchangeable hydrogen storage mounted in a trolley or in a cradle for a plane for onboard applications.

Abstract: An de-icing system comprising a shield that is configured to deform in a pre-determined way that de-bonds accreted ice. In some embodiments, the shield has a variable (non-uniform) stiffness across its width and/or length such that it undergoes a twist-like or other suitable deformation when subjected to a force. In some embodiments, the system includes a plurality of electro-mechanical actuators configured to generate the force applied to the shield.

Abstract: Described are reading light units for a passenger service unit in an overhead panel above a number of passenger seats, including a reading light having a light source for emitting light to a passenger seat, an automatic adjustment arrangement, a beam forming element for adjusting the light beam geometrical properties, and a light forming element for adjusting the light optical properties.

Abstract: The invention relates to a service device having a system of a gasper module and a lighting module for a passenger service unit of an aircraft, comprising: a lighting source in a housing of the lighting module for providing light and a gasper orifice in a housing of the gasper module for supply of gasper air, wherein the lighting module and the gasper module are assembled in a housing assembly of the service device, wherein the housing assembly is adapted to hold the lighting module and the gasper module essentially around an axis (Z) of the housing assembly.

Abstract: Described are elastic tubular devices including an inner tube (23) made of an elastic and gas impermeable material; and a sheath (21) surrounding the inner tube and made of a woven cloth of flame resistant meta-aramid yarns, wherein the tubular device has a longitudinal extension of at least approximately 1.4 when inflated by a gas having a pressure of at least approximately 0.5 bar.

Abstract: There is provided a regulation valve for a life support system for use in an aircraft cabin. The valve may have a gas inlet, an air mask supply outlet connected to the gas inlet, and a pressure vest branch interconnected between the gas inlet and an opening. The valve may further have a decompression valve adapted to inhibit gas flow from the pressure vest branch to the air mask supply outlet if pressure in the aircraft cabin decreases below a predetermined value, a one-way valve adapted to inhibit gas flow from the pressure vest branch to the air mask supply outlet at a predetermined pressure difference between the pressure vest branch and the gas inlet, and a one-way dump valve adapted to direct gas from the pressure vest branch to the environment at the predetermined pressure difference between the pressure vest branch and the gas inlet.