20results about "Emergency oxygen systems" patented technology

A breathing gas supply system (10), potentially for combat aircraft, operative to decrease hypoxia and asynchronous breathing and to conserve breathing gases. An input valve (26) selectively permits breathing gas to fill a flexible gas reservoir (34) through a fluidic connector (28). Breathing gas can be maintained at an elevated pressure. The fluidic connector (28) delivers gas to an output interface (14), such as an oxygen mask (14). An inspiratory valve (30) is permitted to open when inspiration is sensed by an inspiratory sensor (32), and an expiratory valve (48) is permitted to open when expiration is sensed by an expiratory sensor (32). The inspiratory and expiratory sensors (32) can be separate or embodied as an inspiratory-expiratory sensor (32). A sensor reservoir (58) fluidically open to a volume between the output interface (14) and the face of the user can expand or compress to indicate inspiration or expiration. The inspiratory and expiratory valves (30, 48) can be electromagnetically operated.

Apparatus for supplying oxygen to a vehicle user, comprising a source of pressurized respiratory gas containing oxygen-enriched air, a flow-regulating and / or pressure-regulating unit, and at least one mask provided for supplying gas to the respiratory tract of said user, the regulating unit comprising at least one inlet connected to the source and at least one outlet connected to the mask, the regulating unit being configured to regulate the flow and / or the pressure of the respiratory gas supplied to the mask according to the respiratory demand of the user, the apparatus comprising at least one sensor measuring the pressure and / or the flow of respiratory gas delivered by the regulating unit to the mask, and an electronic data storage and processing unit configured to receive the measurements from the at least one sensor and to calculate, from these measurements, the frequency of the gas flows supplied to the mask and corresponding to the respiratory frequency of the user, to compare this calculated frequency against a threshold frequency and, when this calculated frequency is greater than the threshold frequency, to generate an audible and / or visual and / or vibratory warning signal.

A monitoring system for pilots or co-pilots of aircraft is described. Gas concentrations can be measured using sensors. A control unit, in conjunction with a pressure sensor, is able to determine the pressure in the pilot's or co-pilot's breathing mask by means of a measurement maneuver (200).

The invention relates to a monitoring system (100) for flight staff (99) such as plane pilots, aircraft pilots, pilots, co-pilots or passengers of aircrafts or flight devices such as airplanes or helicopters of civil or military aviation, and passenger airplanes in airline traffic or charter traffic, in particular ultrafast airplanes. A sensor system (60) metrologically captures gas concentrations.

An oxygen system for an aircraft may have a chemical oxygen generator; an oxygen mask; and a tube assembly extending from the chemical oxygen generator to the oxygen mask. The tube assembly may have a first tube and a second tube. The first tube defines a fluid conduit that fluidly couples the chemical oxygen generator to the oxygen mask in response to being in use. The second tube may be configured to house a plurality of lights therein.

A piezoelectric actuator controlled smart flow regulator (300) is provided. The piezoelectric actuator controlled smart flow regulator includes an inlet chamber (302) and an actuator chamber (304). The inlet chamber includes an inlet port (310). The actuator chamber includes an exit port (312), a sealing disc (316, 416), and at least one piezoelectric actuator (318). The at least one piezoelectric actuator is coupled to the sealing disc. In a deactivated state, the sealing disc is in contact with the inlet port such that oxygen is prevented from flowing through the actuator chamber. In an activated state, responsive to receiving a voltage, the at least one piezoelectric actuator is configured to restrict thereby translating a center of the sealing disc away from the inlet port and provide an oxygen flow through the inlet port to the exit port.

A hydrogen accumulation control system for monitoring and controlling leaked hydrogen within an interior space, in particular of an aircraft, comprises a hydrogen detection system installed within the interior space and configured to detect the presence of gaseous hydrogen in the interior space and to provide occurrence data on the detected hydrogen within the interior space; a system control configured to assess the occurrence data and to determine and initiate a remedial procedure for reduction of the detected hydrogen within the interior space; and a venting system configured to vent the interior space from the detected hydrogen according to the remedial procedure.

A piezoelectric actuator controlled smart flow regulator is provided. The piezoelectric actuator controlled smart flow regulator includes an inlet chamber and an actuator chamber. The inlet chamber includes an inlet port. The actuator chamber includes an exit port, a sealing disc, and at least one piezoelectric actuator. The at least one piezoelectric actuator is coupled to the sealing disc. In a deactivated state, the sealing disc is in contact with the inlet port such that oxygen is prevented from flowing through the actuator chamber. In an activated state, responsive to receiving a voltage, the at least one piezoelectric actuator is configured to restrict thereby translating a center of the sealing disc away from the inlet port and provide an oxygen flow through the inlet port to the exit port.

A breathing gas supply system, potentially for combat aircraft, operative to decrease hypoxia and asynchronous breathing and to conserve breathing gases. An input valve selectively permits breathing gas to fill a flexible gas reservoir through a fluidic connector. Breathing gas can be maintained at an elevated pressure. The fluidic connector delivers gas to an output interface, such as an oxygen mask. An inspiratory valve is permitted to open when inspiration is sensed by an inspiratory sensor, and an expiratory valve is permitted to open when expiration is sensed by an expiratory sensor. The inspiratory and expiratory sensors can be separate or embodied as an inspiratory-expiratory sensor. A sensor reservoir fluidically open to a volume between the output interface and the face of the user can expand or compress to indicate inspiration or expiration. The inspiratory and expiratory valves can be electromagnetically operated.

An aircraft oxygen supply system includes at least one oxygen mask, an oxygen supply, and a pressure reducer, interposed between the oxygen supply and the at least one oxygen mask. The pressure reducer includes a housing, a piston, which is axially movable within the housing a high pressure inlet, which is provided on a high pressure side of the housing and which is coupled to the oxygen supply, a pressure reducing gas flow path, connecting the high pressure inlet and an axial gas flow channel within the piston, a reduced pressure outlet, which is provided on a reduced pressure side of the housing and to which the axial gas flow channel opens, and a pressure control chamber, which extends radially from the reduced pressure outlet and which is interposed between the housing and a reduced pressure end face of the piston.

Pneumatic air systems for use onboard aircraft include a compressor (102) configured to receive air from an air supply (108) and increase a pressure of said received air to generate compressed air, a heat exchanger (112) configured to receive the compressed air as a first working fluid and a treating air as a second working fluid, the heat exchanger (112) configured to convert the compressed air to compressed and temperature treated air, one or more aircraft systems (114a-c) configured to receive the compressed and temperature treated air, and a surge prevention circuit (138) arranged to prevent surge of air at the compressor, wherein the surge prevention circuit (138) comprises a mechanical valve (140) that is actuated based on a detected pressure within a sense line (142) operably coupled to the mechanical valve (140).

A device for regulating breathing gas delivered to a user, comprising a gas circuit comprising a main line (2) having at least an upstream end intended to be connected to at least one gas source (6, 5) and a downstream end intended to be connected to at least one user station (7) such as a mask (7), the main line (2) comprising at least one electromechanical control valve (3) configured to regulate the gas pressure between the upstream and the downstream, the circuit comprising a secondary line (8) comprising an upstream end intended to be connected to at least one gas source (6, 5) and a downstream end intended to be connected to the same user station(s) (7), the secondary line (8) comprising at least one auxiliary member (10) for regulating the gas flow, the device comprising a switching system (11, 4) configured to control the flow of gas between the upstream and the downstream of the circuit via the main line (2) or via the secondary line (8), characterised in that the auxiliary member (10) for regulating the secondary line (8) is a pneumatic pressure regulator.

A monitoring system for pilots or co-pilots of aircraft is described. Gas concentrations can be measured using sensors. A control unit, in conjunction with a pressure sensor, is able to determine the pressure in the pilot's or co-pilot's breathing mask by means of a measurement maneuver (200).

An emergency oxygen system for an internal cabin of a vehicle includes a housing including one or more compartments. One or more oxygen assemblies include a mask and a fluid conduit. The mask is configured to be stowed within and deployed from the one or more compartments. A door is moveably secured to the housing. The door is configured to pivot in an outboard direction from a closed position to an open position during a deployment event. One or more pouches can be secured to an interior surface of the door. Coiled tubing of the fluid conduit is retained by the one or more pouches when the mask is stowed within the one or more compartments. An alert device can be operatively coupled to the one or more oxygen assemblies. The alert device is configured to emit a response indicating that oxygen is flowing to the mask.

A manifold assembly is provided. The manifold assembly includes a pressurized gas manifold, a manifold insert, an initiator, and a mechanical restrictor. The manifold insert is mechanically coupled to the pressurized gas manifold. The initiator is mechanically coupled to the manifold insert. The initiator includes a lance and an initiator mechanism. The initiator mechanism is configured to initiate thereby causing the lance to translate the lance to a deployed state and rupture a rupture disc. The mechanical restrictor is configured to securely lock the lance in the deployed state.

A monitoring system (100') for pilots or co-pilots (99) of aircraft is described. Gas concentrations are measured using sensors (60). Furthermore, an accelerometer (61) is provided in or on the monitoring system (100), which serves as an input element for the pilot (99) or co-pilot, for example, as a panic button or for marking situations on the monitoring system (100).

A monitoring system (100') for pilots or co-pilots (99) of aircraft is described. Gas concentrations are measured using sensors (60). Furthermore, an accelerometer (61) is provided in or on the monitoring system (100), which serves as an input element for the pilot (99) or co-pilot, for example, as a panic button or for marking situations on the monitoring system (100).

An aircraft oxygen supply system (2) comprises at least one oxygen mask (12), an oxygen supply (20), and a pressure reducer (26), interposed between the oxygen supply (20) and the at least one oxygen mask (12). The pressure reducer (26) comprises a housing (28), a piston (30), which is axially movable within the housing (28), a high pressure inlet (32), which is provided on a high pressure side of the housing (28) and which is coupled to the oxygen supply (20), a pressure reducing gas flow path (34), connecting the high pressure inlet and (32) an axial gas flow channel (36) within the piston (30), a reduced pressure outlet (38), which is provided on a reduced pressure side of the housing (28) and to which the axial gas flow channel (36) opens, and a pressure control chamber (40), which extends radially from the reduced pressure outlet (38) and which is interposed between the housing (28) and a reduced pressure end face (46) of the piston (30).

A head armature for a respiratory system includes a cradle and a retention mechanism. The cradle is configured to receive a respiratory mask assembly in a stand-by position. The retention mechanism is configured to detachably connect the respiratory mask assembly with the head armature such that the respiratory mask assembly is movable from the stand-by position to a use position while connected to the head armature and such that the respiratory mask assembly is selectively detachable from the head armature in a stand-alone configuration whereby the respiratory mask assembly is disconnected from the head armature. In the use position, the respiratory mask assembly is configured to provide oxygen to a user. The head armature is configured to be worn on a head of the user such that the cradle is between the respiratory mask assembly and the user's head when the respiratory mask assembly is in the stand-by position.

Redundant electrochemical systems and methods for vehicles are described. The systems include a first electrochemical device located at a first position on the vehicle wherein the first electrochemical device is configured to generate at least one of inert gas, oxygen, and electrical power and a second electrochemical device located at a second position on the vehicle wherein the second electrochemical device is configured to generate at least one of inert gas, oxygen, and electrical power. The first electrochemical device is configured to operate in a first mode during normal operation of the vehicle and a second mode when the second electrochemical device fails, wherein in the second mode, the first electrochemical device provides the at least one of inert gas, oxygen, and electrical power for at least one vehicle critical system of the vehicle.