37results about "Emergency oxygen systems" patented technology

Methods, apparatuses, and systems for mechanically releasing a predetermined amount of supplemental oxygen to a user via a mechanical initiator are disclosed with the release of the amount of supplemental oxygen based on and in response to the combined factors of a user's determined oxygen consumption based on sensing a user's inhalation combined with determining the ambient pressure in the area of the user.

There is provided an apparatus for preparing a ventilation gas mixture for pilots and crew of aircraft, the apparatus comprising a first gas mixer feed configured to receive exhaled air from a person, wherein the exhaled air comprises carbon dioxide, a second gas mixer feed configured to receive an air mixture comprising at least one gas, and a gas mixing device configured to receive the exhaled air and the air mixture from the first and second gas mixer feeds and combine the exhaled air with the air mixture in the gas mixing device to form a ventilation gas mixture. The apparatus further comprises a pressure adjuster configured to increase the pressure of the exhaled air in the first gas mixer feed so that it substantially matches the pressure of the air mixture in the second gas mixer feed.

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.

The invention relates to an oxygen mask for supplying oxygen to a person, which can be modified for use on differently sized faces. The oxygen mask has a holding frame, which has a first cross-brace and a second cross-brace, a substantially gas-impermeable material arranged on the holding frame and which can be stretched between the first cross-brace and the second cross-brace, a headband connected to the holding frame, an exhalation valve arranged on the material and penetrating the material, and an oxygen supply line for providing oxygen to an inside of the oxygen mask, wherein the first cross-brace and the second cross-brace are arranged in two lateral holders, which are opposite each other, wherein at least the first cross-brace is flexible and wherein the distance of the lateral holders to each other is adjustable at least between a first and a second distance.

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 apparatus for preparing a ventilation gas mixture to a user comprises: a gas mixing device configured to receive oxygen through a first gas feed, the gas mixing device being further configured to received exhaled air from a person; a gas reservoir configured to receive the exhaled air from the gas mixing device through a second gas feed, wherein the gas reservoir is further configured to re-supply the exhaled air to the gas mixing device through the second gas feed; an altitude sensor configured to determine altitude information; a control system configured to receive the altitude information from the altitude sensor and further configured to control the flow of oxygen through the first gas feed based on the received altitude information; wherein the gas mixing device is arranged to combine the oxygen received through the first gas feed with the re-supplied exhaled air received through the second gas feed in order to prepare a ventilation gas mixture.

An oxygen pressure relief and ventilation system includes a flow fuse fluidly coupled downstream of a pressure regulator. The pressure regulator is operatively coupled to an oxygen tank, and the oxygen tank is located in an unpressurized compartment of an aircraft. A pressure relief valve is fluidly coupled downstream of the flow fuse. A ventilation pathway fluidly couples the unpressurized compartment with a pressurized compartment. The flow fuse and the pressure relief valve are configured to cooperatively mitigate downstream flow of pressurized oxygen if the pressure regulator fails. The ventilation pathway is configured to allow air from the pressurized compartment to pass through to the unpressurized compartment for diluting a concentrated oxygen in the unpressurized compartment.

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.

The invention relates to a method for controlling an oxygen tank (1) for an aircraft (10), the method being implemented by an onboard computer (12) of the aircraft (10), the method comprising the steps of: - repeatedly measuring a current value of a volume of oxygen in the tank (1) and storing the current value in a database; - calculating a mean oxygen consumption rate over an observation period on the basis of the current values stored in the database; - comparing the mean rate with a predetermined mean rate limit; - detecting a potential state of active oxygen consumption from the tank (1) over the observation period; and - flagging a leak from the tank if the mean oxygen consumption rate is higher than the predetermined mean rate limit and if no state of active consumption has been detected over the observation period.

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.

The invention belongs to civil aircraft passenger emergency oxygen supply, and particularly relates to a distributed electronic adjustment passenger emergency oxygen unit. Comprising a decentralized oxygen bottle assembly, an electromagnetic plunger latch, an oxygen supply control regulator, a passenger oxygen mask and a passenger oxygen mask box, the decentralized oxygen bottle assembly, the electromagnetic plunger latch and the oxygen supply control regulator are fixed in the passenger oxygen mask box, and the decentralized oxygen bottle assembly is connected with the oxygen supply control regulator through a pipeline. The oxygen control regulator is connected with the passenger oxygen mask through a pipeline, and the oxygen supply control regulator is connected with and controls the electromagnetic plunger latch through a cable; a switch of the electromagnetic plunger latch is used for controlling a small door of the passenger oxygen mask box, and the passenger oxygen mask falls after the small door is opened; a mooring rope is arranged on the passenger oxygen mask and is connected with the distributed oxygen bottle assembly; the oxygen supply control regulator is electrically connected with the onboard jettisoning control circuit, the onboard BIT module and the onboard avionics system and used for controlling oxygen supply to the passenger oxygen mask according to the onboard signals.

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 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.

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 monitoring system (100) for the flight crew (99), for example the pilot, the aviation pilot, the pilot, the co-pilot, of an aircraft or a flying machine, for example an airplane or a helicopter of civil or military aviation, a passenger plane in scheduled or charter flights, in particular also a hypersonic aircraft, is described. By means of a sensor device (60), the air concentration is detected with measuring technology.

The invention relates to an oxygen mask for supplying oxygen to a person, which can be modified for use on differently sized faces. The oxygen mask has a holding frame, which has a first cross-brace and a second cross-brace, a substantially gas-impermeable material arranged on the holding frame and which can be stretched between the first cross-brace and the second cross-brace, a headband connected to the holding frame, an exhalation valve arranged on the material and penetrating the material, and an oxygen supply line for providing oxygen to an inside of the oxygen mask, wherein the first cross-brace and the second cross-brace are arranged in two lateral holders, which are opposite each other, wherein at least the first cross-brace is flexible and wherein the distance of the lateral holders to each other is adjustable at least between a first and a second distance.

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.

The application discloses an aircraft oxygen load allocation method based on a dynamic database, relates to the field of aviation system engineering and control engineering, and comprises the following steps: a digital twin model is established by using simulation software, the current state of aircraft oxygen is obtained, oxygen demand under different flight stages is preset, a multi-physical field coupling optimization is performed on the digital twin model by using an optimization algorithm, the optimized result is fed back to the dynamic database, an oxygen allocation scheme is obtained, a federal learning technology is used to train an oxygen demand model, oxygen demand in future flight stages is predicted, and a self-repairing mechanism is designed and deployed according to the prediction result; and the application realizes real-time monitoring of oxygen consumption by using a dynamic reconstruction algorithm, intervenes when the oxygen allocation scheme does not match the oxygen consumption, and optimizes the oxygen allocation scheme, so that the demand of emergent conditions is met, and the fault tolerance and reliability are greatly increased.

A vehicle includes an internal cabin. A plurality of passenger service units (PSUs) are within the internal cabin. An emergency oxygen system is within the internal cabin. The emergency oxygen system is separate and distinct from the plurality of PSUs. A method includes providing a plurality of passenger service units (PSUs) within an internal cabin of a vehicle, and providing an emergency oxygen system within the internal cabin, wherein the emergency oxygen system is separate and distinct from the plurality of PSUs.

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.

A monitoring system (100″) is for aeronautical personnel (99), such as aircraft operators, pilots, co-pilots or passengers of airplanes or aircraft, such as aircraft or helicopters of civil or military aviation, passenger aircraft in scheduled or charter traffic, in particular also ultra-fast aircraft. The monitoring system includes a sensor system (60) for a measurement-based monitoring of the gas concentration. The operation of the monitoring system (100″) can be configured by an external input / output unit (450) or an external output unit (460).

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.

An aircraft passenger service unit, which is configured for being installed in a passenger cabin of an aircraft. The unit includes at least two near field communication interfaces, wherein each of the at least two near field communication interfaces is configured for a wireless exchange of messages with a corresponding near field communication interface of a neighboring aircraft passenger service unit. The messages include information that identifies the aircraft passenger service unit and the near field communication interface sending the respective message.

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).